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© European Organisation for the Safety of Air Navigation EUROCONTROL 2010 This document is published by EUROCONTROL in the interest of the exchange of information. It may be copied in whole or in part providing that the copyright notice and disclaimer are included. The information contained in this document may not be modified without prior written permission from EUROCONTROL. EUROCONTROL makes no warranty, either implied or express, for the information contained in this document, neither does it assume any legal liability or responsibility for the accuracy, completeness or usefulness of this information. EUROPEAN ORGANISATION FOR THE SAFETY OF AIR NAVIGATION EUROCONTROL EXPERIMENTAL CENTRE REVISION OF ATMOSPHERE MODEL IN BADA AIRCRAFT PERFORMANCE MODEL EEC Technical Report No. 2010-001 Project: BADA Public Issued: February 2010 EUROCONTROL

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© European Organisation for the Safety of Air Navigation EUROCONTROL 2010 This document is published by EUROCONTROL in the interest of the exchange of information. It may be copied in whole or in part

providing that the copyright notice and disclaimer are included. The information contained in this document may not be modified without prior written permission from EUROCONTROL.

EUROCONTROL makes no warranty, either implied or express, for the information contained in this document, neither does it assume any legal liability or responsibility for the accuracy, completeness or usefulness of this information.

EUROPEAN ORGANISATION FOR THE SAFETY OF AIR NAVIGATION

EUROCONTROL EXPERIMENTAL CENTRE

REVISION OF ATMOSPHERE MODEL IN BADA AIRCRAFT PERFORMANCE MODEL

EEC Technical Report No. 2010-001

Project: BADA

Public Issued: February 2010

EUROCONTROL

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REPORT DOCUMENTATION PAGE

Reference EEC Note/Report No. 2010/001

Security Classification Unclassified

Originator: CND/VIF/ACP

Originator (Corporate Author) Name/Location: EUROCONTROL Experimental Centre B.P.15 F – 91222 Brétigny-sur-Orge CEDEX FRANCE Telephone : +33 1 69 88 75 00 Internet : www.eurocontrol.int

Sponsor EUROCONTROL

Sponsor (Contract Authority) Name/Location EUROCONTROL Agency Rue de la Fusée, 96 B –1130 BRUXELLES Telephone : +32 2 729 9011 Internet : www.eurocontrol.int

TITLE : REVISION OF ATMOSPHERE MODEL IN BADA AIRCRAFT PERFORMANCE MODEL

Author D. Poles

Date

02/2010 Pages

xvi+146 Figures

3 Tables 172

Annexes 2

References 7

Project BADA

Task no. sponsor CND/VIR/ACP

Period 07/09 to 12/09

Distribution Statement: (a) Controlled by: Head of Section (b) Distribution : Public Restricted Confidential (c) Copy to NTIS: YES / NO

Descriptors (keywords) :

BADA, aircraft performance model, BADA atmosphere model, International Standard Atmosphere (ISA)

Abstract :

This document provides details about the newly developed BADA atmosphere model. It presents the main differences compared to the atmosphere model currently implemented and provides information on impact of introducing the changes in the BADA family 3 model algorithms. Benefits in terms of improved aircraft performance parameters accuracy and ensured consistency between the atmosphere models used by aircraft performance models and aircraft Flight Management System are also identified. The new BADA atmosphere model has been used in the identification process of the BADA revision 3.7 and it will be used in all subsequent revisions of BADA family 3. The aircraft performance coefficients of the BADA 3.7 and onwards are compatible and may be used with both atmosphere models. Although the implementation decision is left to the users of the BADA family 3 users, the implementation of the new model is highly recommended by the BADA project team at EUROCONTROL.

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 v

FOREWORD

This document provides details about the newly developed BADA atmosphere model. It presents the main differences compared to the atmosphere model currently implemented and provides information on impact of introducing the changes in the BADA family 3 model algorithms. Benefits in terms of improved aircraft performance parameters accuracy and ensured consistency between the atmosphere models used by aircraft performance models and aircraft Flight Management System are also identified. The new BADA atmosphere model has been used in the identification process of the BADA revision 3.7 and it will be used in all subsequent revisions of BADA family 3. The aircraft performance coefficients of the BADA 3.7 and onwards are compatible and may be used with both atmosphere models. Although the implementation decision is left to the users of the BADA family 3 users, the implementation of the new model is highly recommended by the BADA project team at EUROCONTROL.

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TABLE OF CONTENTS

FOREWORD ...................................................................................................................... V

LIST OF APPENDICES ................................................................................................... VIII

LIST OF FIGURES .......................................................................................................... VIII

LIST OF TABLES ............................................................................................................ VIII

LIST OF ABBREVIATIONS ............................................................................................ XIII

REFERENCES ................................................................................................................. XV

1. INTRODUCTION ........................................................................................................... 1

2. INTERNATIONAL STANDARD ATMOSPHERE (ISA) MODEL ................................... 3 2.1. THE EQUATION OF THE STATIC ATMOSPHERE AND THE PERFECT GAS LAW ... 3

2.2. GEOPOTENTIAL AND GEODETIC ALTITUDES .......................................................... 3

2.3. PHYSICAL CHARACTERISTICS OF THE ATMOSPHERE AT THE MEAN SEA LEVEL ..................................................................................................................................... 5

2.4. TEMPERATURE AND VERTICAL TEMPERATURE GRADIENT ................................. 5

2.5. PRESSURE .................................................................................................................. 6

2.6. DENSITY ...................................................................................................................... 7

2.7. SPEED OF SOUND ...................................................................................................... 7

3. NEW BADA ATMOSPHERE MODEL ........................................................................... 9 3.1. DEFINITIONS ............................................................................................................... 9

3.2. HYPOTHESES ........................................................................................................... 11

3.3. RELATIONSHIP BETWEEN GEOPOTENTIAL AND GEOPOTENTIAL PRESSURE ALTITUDES ................................................................................................................ 12

3.4. EXPRESSIONS .......................................................................................................... 13

4. KEY DIFFERENCES BETWEEN THE OLD AND NEW ATMOSPHERE MODEL ..... 19

5. IMPACT OF CHANGES ON BADA FAMILY 3 ........................................................... 21

6. BENEFITS OF IMPLEMENTING THE NEW ATMOSPHERE MODEL ....................... 25

7. CONCLUSIONS AND RECOMMENDATIONS ........................................................... 27

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LIST OF APPENDICES

APPENDIX A: REVISION 3.7 NON-ISA ACCURACY TABLES ................................ 31

APPENDIX B: THE NEW BADA ATMOSPHERE MODEL TABLE DATA .............. 127

LIST OF FIGURES

Figure 4-1: The relationship between tropopause altitude and temperature for the old model ...... 19Figure 4-2: The relationship between geopotential pressure altitude and temperature for the new

model .......................................................................................................................... 20Figure 4-3: The relationship between geopotential altitude and temperature for the new model ... 20

LIST OF TABLES

Table 2-1: Temperatures and vertical gradients ............................................................................. 6Table 5-1: New BADA atmosphere model impact ........................................................................ 22Table A-1: A30B with the new atmosphere model ........................................................................ 32Table A-2: A30B with the old atmosphere model ......................................................................... 32Table A-3: A310 with the new atmosphere model ........................................................................ 33Table A-4: A310 with the old atmosphere model .......................................................................... 33Table A-5: A319 with the new atmosphere model ........................................................................ 34Table A-6: A319 with the old atmosphere model .......................................................................... 34Table A-7: A320 with the new atmosphere model ........................................................................ 35Table A-8: A320 with the old atmosphere model .......................................................................... 35Table A-9: A321 with the new atmosphere model ........................................................................ 36Table A-10: A321 with the old atmosphere model ........................................................................ 36Table A-11: A332 with the new atmosphere model ...................................................................... 37Table A-12: A332 with the old atmosphere model ........................................................................ 37Table A-13: A333 with the new atmosphere model ...................................................................... 38Table A-14: A333 with the old atmosphere model ........................................................................ 38Table A-15: A343 with the new atmosphere model ...................................................................... 39Table A-16: A343 with the old atmosphere model ........................................................................ 39Table A-17: A346 with the new atmosphere model ...................................................................... 40Table A-18: A346 with the old atmosphere model ........................................................................ 41Table A-19: A388 with the new atmosphere model ...................................................................... 42

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Table A-20: A388 with the old atmosphere model ........................................................................ 43Table A-21: AT43 with the new atmosphere model ...................................................................... 44Table A-22: AT43 with the old atmosphere model ........................................................................ 44Table A-23: AT45 with the new atmosphere model ...................................................................... 45Table A-24: AT45 with the old atmosphere model ........................................................................ 45Table A-25: AT72 with the new atmosphere model ...................................................................... 46Table A-26: AT72 with the old atmosphere model ........................................................................ 46Table A-27: ATP with the new atmosphere model ........................................................................ 47Table A-28: ATP with the old atmosphere model ......................................................................... 47Table A-29: B462 with the new atmosphere model ...................................................................... 48Table A-30: B462 with the old atmosphere model ........................................................................ 48Table A-31: B712 with the new atmosphere model ...................................................................... 49Table A-32: B712 with the old atmosphere model ........................................................................ 49Table A-33: B722 with the new atmosphere model ...................................................................... 50Table A-34: B722 with the old atmosphere model ........................................................................ 50Table A-35: B732 with the new atmosphere model ...................................................................... 51Table A-36: B732 with the old atmosphere model ........................................................................ 51Table A-37: B733 with the new atmosphere model ...................................................................... 52Table A-38: B733 with the old atmosphere model ........................................................................ 52Table A-39: B734 with the new atmosphere model ...................................................................... 53Table A-40: B734 with the old atmosphere model ........................................................................ 53Table A-41: B735 with the new atmosphere model ...................................................................... 54Table A-42: B735 with the old atmosphere model ........................................................................ 54Table A-43: B736 with the new atmosphere model ...................................................................... 55Table A-44: B736 with the old atmosphere model ........................................................................ 55Table A-45: B737 with the new atmosphere model ...................................................................... 56Table A-46: B737 with the old atmosphere model ........................................................................ 56Table A-47: B738 with the new atmosphere model ...................................................................... 57Table A-48: B738 with the old atmosphere model ........................................................................ 57Table A-49: B742 with the new atmosphere model ...................................................................... 58Table A-50: B742 with the old atmosphere model ........................................................................ 58Table A-51: B743 with the new atmosphere model ...................................................................... 59Table A-52: B743 with the old atmosphere model ........................................................................ 59Table A-53: B744 with the new atmosphere model ...................................................................... 60Table A-54: B744 with the old atmosphere model ........................................................................ 60Table A-55: B752 with the new atmosphere model ...................................................................... 61Table A-56: B752 with the old atmosphere model ........................................................................ 61Table A-57: B753 with the new atmosphere model ...................................................................... 62

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Table A-58: B753 with the old atmosphere model ........................................................................ 62Table A-59: B762 with the new atmosphere model ...................................................................... 63Table A-60: B762 with the old atmosphere model ........................................................................ 63Table A-61: B763 with the new atmosphere model ...................................................................... 64Table A-62: B763 with the old atmosphere model ........................................................................ 64Table A-63: B764 with the new atmosphere model ...................................................................... 65Table A-64: B764 with the old atmosphere model ........................................................................ 65Table A-65: B772 with the new atmosphere model ...................................................................... 66Table A-66: B772 with the old atmosphere model ........................................................................ 66Table A-67: B773 with the new atmosphere model ...................................................................... 67Table A-68: B773 with the old atmosphere model ........................................................................ 67Table A-69: BE9L with the new atmosphere model ...................................................................... 68Table A-70: BE9L with the old atmosphere model ........................................................................ 68Table A-71: BE20 with the new atmosphere model ...................................................................... 69Table A-72: BE20 with the old atmosphere model ........................................................................ 69Table A-73: BE58 with the new atmosphere model ...................................................................... 70Table A-74: BE58 with the old atmosphere model ........................................................................ 70Table A-75: C130 with the new atmosphere model ...................................................................... 71Table A-76: C130 with the old atmosphere model ........................................................................ 71Table A-77: C510 with the new atmosphere model ...................................................................... 72Table A-78: C510 with the old atmosphere model ........................................................................ 73Table A-79: C550 with the new atmosphere model ...................................................................... 74Table A-80: C550 with the old atmosphere model ........................................................................ 74Table A-81: C560 with the new atmosphere model ...................................................................... 75Table A-82: C560 with the old atmosphere model ........................................................................ 75Table A-83: C750 with the new atmosphere model ...................................................................... 76Table A-84: C750 with the old atmosphere model ........................................................................ 76Table A-85: CL60 with the new atmosphere model ...................................................................... 77Table A-86: CL60 with the old atmosphere model ........................................................................ 78Table A-87: CRJ1 with the new atmosphere model ...................................................................... 79Table A-88: CRJ1 with the old atmosphere model ....................................................................... 79Table A-89: CRJ2 with the new atmosphere model ...................................................................... 80Table A-90: CRJ2 with the old atmosphere model ....................................................................... 80Table A-91: CRJ9 with the new atmosphere model ...................................................................... 81Table A-92: CRJ9 with the old atmosphere model ....................................................................... 81Table A-93: D228 with the new atmosphere model ...................................................................... 82Table A-94: D228 with the old atmosphere model ........................................................................ 82Table A-95: D328 with the new atmosphere model ...................................................................... 83Table A-96: D328 with the old atmosphere model ........................................................................ 83

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Table A-97: DA42 with the new atmosphere model ...................................................................... 84Table A-98: DA42 with the old atmosphere model ....................................................................... 84Table A-99: DH8A with the new atmosphere model ..................................................................... 85Table A-100: DH8A with the old atmosphere model ..................................................................... 85Table A-101: DH8C with the new atmosphere model ................................................................... 86Table A-102: DH8C with the old atmosphere model ..................................................................... 86Table A-103: DH8D with the new atmosphere model ................................................................... 87Table A-104: DH8D with the old atmosphere model ..................................................................... 87Table A-105: E120 with the new atmosphere model .................................................................... 88Table A-106: E120 with the old atmosphere model ...................................................................... 88Table A-107: E135 with the new atmosphere model .................................................................... 89Table A-108: E135 with the old atmosphere model ...................................................................... 90Table A-109: E145 with the new atmosphere model .................................................................... 91Table A-110: E145 with the old atmosphere model ...................................................................... 92Table A-111: E170 with the new atmosphere model .................................................................... 93Table A-112: E170 with the old atmosphere model ...................................................................... 94Table A-113: E190 with the new atmosphere model .................................................................... 95Table A-114: E190 with the old atmosphere model ...................................................................... 96Table A-115: EA50 with the new atmosphere model .................................................................... 97Table A-116: EA50 with the old atmosphere model ...................................................................... 98Table A-117: F27 with the new atmosphere model ...................................................................... 99Table A-118: F27 with the old atmosphere model ........................................................................ 99Table A-119: F50 with the new atmosphere model .................................................................... 100Table A-120: F50 with the old atmosphere model ...................................................................... 100Table A-121: F70 with the new atmosphere model .................................................................... 101Table A-122: F70 with the old atmosphere model ...................................................................... 101Table A-123: F100 with the new atmosphere model .................................................................. 102Table A-124: F100 with the old atmosphere model .................................................................... 102Table A-125: F900 with the new atmosphere model .................................................................. 103Table A-126: F900 with the old atmosphere model .................................................................... 103Table A-127: FA50 with the new atmosphere model .................................................................. 104Table A-128: FA50 with the old atmosphere model .................................................................... 104Table A-129: H25A with the new atmosphere model .................................................................. 105Table A-130: H25A with the old atmosphere model ................................................................... 105Table A-131: JS31 with the new atmosphere model .................................................................. 106Table A-132: JS31 with the old atmosphere model .................................................................... 106Table A-133: JS41 with the new atmosphere model .................................................................. 107Table A-134: JS41 with the old atmosphere model .................................................................... 107

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Table A-135: LJ35 with the new atmosphere model ................................................................... 108Table A-136: LJ35 with the old atmosphere model ..................................................................... 108Table A-137: LJ45 with the new atmosphere model ................................................................... 109Table A-138: LJ45 with the old atmosphere model ..................................................................... 109Table A-139: MD11 with the new atmosphere model ................................................................. 110Table A-140: MD11 with the old atmosphere model ................................................................... 111Table A-141: MD82 with the new atmosphere model ................................................................. 112Table A-142: MD82 with the old atmosphere model ................................................................... 113Table A-143: MD83 with the new atmosphere model ................................................................. 114Table A-144: MD83 with the old atmosphere model ................................................................... 115Table A-145: P28A with the new atmosphere model .................................................................. 116Table A-146: P28A with the old atmosphere model .................................................................... 116Table A-147: PA34 with the new atmosphere model .................................................................. 117Table A-148: PA34 with the old atmosphere model .................................................................... 117Table A-149: RJ85 with the new atmosphere model .................................................................. 118Table A-150: RJ85 with the old atmosphere model .................................................................... 118Table A-151: SB20 with the new atmosphere model .................................................................. 119Table A-152: SB20 with the old atmosphere model .................................................................... 119Table A-153: SF34 with the new atmosphere model .................................................................. 120Table A-154: SF34 with the old atmosphere model .................................................................... 120Table A-155: SH36 with the new atmosphere model .................................................................. 121Table A-156: SH36 with the old atmosphere model ................................................................... 121Table A-157: SW4 with the new atmosphere model ................................................................... 122Table A-158: SW4 with the old atmosphere model ..................................................................... 122Table A-159: T134 with the new atmosphere model .................................................................. 123Table A-160: T134 with the old atmosphere model .................................................................... 123Table A-161: T154 with the new atmosphere model .................................................................. 124Table A-162: T154 with the old atmosphere model .................................................................... 124Table A-163: TRIN with the new atmosphere model .................................................................. 125Table A-164: TRIN with the old atmosphere model .................................................................... 125Table B-1: ISA -20 table data ..................................................................................................... 128Table B-2: ISA -10 table data ..................................................................................................... 131Table B-3: ISA table data .......................................................................................................... 134Table B-4: ISA+10 table data ..................................................................................................... 137Table B-5: ISA+20 table data ..................................................................................................... 140Table B-6: ISA+30 table data ..................................................................................................... 143

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LIST OF ABBREVIATIONS

APM Aircraft Performance Model

BADA Base of Aircraft Data

CAS calibrated airspeed

CMB climb

CRZ cruise

DES descent

FMS Flight Management System

ICAO International Civil Aviation Organisation

ISA International Standard Atmosphere

ISO International Organisation for Standardisation

MCMB maximum climb

MSL mean sea level

RMS root mean square

STD standard deviation

TRJ trajectory

TROP tropopause

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REFERENCES

[1] Base of aircraft data (BADA) aircraft performance modelling report - Revision 3.7, EEC Technical Report No. 2009-009, EUROCONTROL EEC, 2009.

[2] AMEBA - Concept Document, EEC Technical Report, EUROCONTROL EEC, 2006. [3] User manual for the base of aircraft data (BADA) – Revision 3.7, EEC Technical Report No.

2009-003, EUROCONTROL EEC, 2009. [4] International standard ISO 2533, Standard atmosphere, Ref. No. 2533-1975 (E),

International Organization for Standardization, 1975. [5] Manual of the ICAO standard atmosphere, Doc 7488/3, 1993. [6] AMEBA – Improvement report, EEC Technical Report, 2005. [7] BADA 4.0 Aircraft Performance Model Toolbox, User Manual v1.3, ECC Note No. 06/09,

2009.

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1. INTRODUCTION

Enhancements to the BADA aircraft performance modelling capabilities have been the subject of research efforts over the past years. The research was based on exploiting today’s aircraft performance resources, data and software, which were not available in the past when BADA was initially developed1

1 Nowadays, aircraft manufacturers develop aircraft performance engineering software that can provide high quality aircraft

performance reference data including other relevant parameters that facilitate aircraft performance models development and validation.

. Encouraging results that demonstrate benefits of using new data resources and provide improvements in various aspects ([2], [6]) of aircraft performance modelling capabilities have been obtained. One of the findings which contribute to the improvements is related to the way the International Standard Atmosphere (ISA) model is applied in the BADA aircraft performance model. Namely, by using detailed aircraft manufacturers performance reference data, some discrepancies were observed between atmospheric properties at non-ISA conditions provided by the atmosphere model currently used by BADA family 3 [1] and the one used by aircraft manufacturers. After having analysed the discrepancies, it was found out that both of the atmosphere models use the same basic principles of the International Standard Atmosphere (ISA), but with different definition of tropopause altitude and temperature gradient. This causes differences in the calculation of some aircraft performance parameters (energy share factor, rate of climb, etc) with a consequent impact on aircraft performance models’ accuracy. Since the aircraft model identification process in BADA family 3 [1] and 4 ([2], [7]) is based on aircraft manufacturers performance reference data for different atmospheric conditions, it is deemed important to ensure consistency between the atmosphere models used by aircraft performance models and aircraft manufacturers. Furthermore, this ensures consistency in calculation of some aircraft performance parameters between simulation tools and aircraft Flight Management System (FMS) for given atmosphere conditions. For this reason, a new BADA atmosphere model was developed in a way that best fits the aircraft performance reference data by including precise modelling of atmosphere for ISA and non-ISA initial conditions (temperature and pressure deviations). Benefits in implementing the new atmosphere model in terms of aircraft horizontal speed, vertical speed and fuel flow were assessed and demonstrated during development of the aircraft models in BADA 3.7. The objectives of this document are to describe the newly developed BADA atmosphere model; identify the main differences compared to the atmosphere model currently implemented (referred to as the old one); provide information on cost (impact of introducing the changes in the BADA family 3 model algorithms) and benefits (improved aircraft performance parameters accuracy).

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The document is organised in 7 sections including Section 1, Introduction. Section 2 contains the ISA atmosphere descriptions on which the new BADA atmosphere model is based. Section 3 describes the new BADA atmosphere model in detail. Key differences between the old and new model are given in Section 4. The impact of the new BADA atmosphere model on BADA operations performance model is described in Section 5. The benefits are discussed in Section 6, while conclusions and recommendations for use are given in section 7. Accuracy tables for all aircraft types developed for BADA revision 3.7, for current and new BADA atmosphere models, are given in Appendix A. In Appendix B, for the new BADA atmosphere model, table data for different conditions are given.

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2. INTERNATIONAL STANDARD ATMOSPHERE (ISA) MODEL

The International Standard Atmosphere (ISA) is an atmospheric model of how the pressure, temperature, density and viscosity of the Earth’s atmosphere change over a wide range of altitude. The International Organisation for Standardisation (ISO) publishes the ISA as an international standard [4]. Another organisations, the International Civil Aviation Organisation (ICAO) publishes an ICAO standard atmosphere [5]. In this section, the basic principles and calculation formulas used in both cases and relevant for aircraft performance modelling activity are presented.

2.1. THE EQUATION OF THE STATIC ATMOSPHERE AND THE PERFECT GAS LAW

Being static with respect to the Earth, the atmosphere is subject to gravity and the conditions of fluidostatic (air static) equilibrium are determined by the following equation:

-dp = ρ g dh (2-1) where p is air pressure, ρ density, g acceleration due to gravity and h geodetic altitude. The perfect gas law relates air pressure, p, to density, ρ, and temperature, T, as follows:

p = ρ R T (2-2) where R is the specific gas constant, R = 287,05287 [m2/Ks2] for dry air.

2.2. GEOPOTENTIAL AND GEODETIC ALTITUDES

In order to characterize pressure distribution in the atmosphere, the gravity potential or geopotential, Φ, should be introduced. The gravity potential characterizes the potential energy of an air particle at a given point, (x, y, z). The equation:

Φ(x, y, z) = const. (2-3) defines a surface of the same potential. Moving along on external normal from any point the change in the gravity potential will be equal to the work performed:

dΦ = g (h) dh (2-4)

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and finally, integrating and dividing by g0, standard acceleration due to gravity, g0 = 9,80665 [m/s2]:

( )∫=Φ

=h

dhhggg

H000

1 (2-5)

where H is numerically equal to the geopotential altitude and h is geodetic altitude. The mean sea level is taken as a reference for readings for both geopotential and geodetic altitude. It can be seen, from (2-5), that in order to relate geopotential and geodetic altitudes it is necessary to find a relationship between acceleration due to gravity, g, and geodetic altitude. It is known that gravity is a vectorial summation of the gravitational attraction and the centrifugal force induced by the earth rotation and it is a complex function of latitude and radial distance from earth’s centre. In general, it is complex and unpractical for use. However, acceleration may be obtained with sufficient accuracy by neglecting centrifugal acceleration and using only Newton’s gravitational law, in which case:

2

0

+

=hr

rgg (2-6)

where r is the nominal earth’s radius, r = 6 325 766 [m] (the earth is considered as a sphere). Combining (2-5) and (2-6) gives the following relationship between geopotential and geodetic altitudes:

hrhrH+

= , Hr

Hrh−

= (2-7)

Note that values of g calculated using the equation (2-6) for the altitude of 60 000 [m] do not differ by more than 0,001 percent from the values calculated using the more accurate equations (2-5) ([4], [5]).

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2.3. PHYSICAL CHARACTERISTICS OF THE ATMOSPHERE AT THE MEAN SEA LEVEL

For the calculation of the ISA atmosphere, the mean sea level is defined as zero altitude with the following initial values for the most important characteristics:

• standard acceleration due to gravity, g0 = 9.80665 [m/s2]; • atmospheric pressure, p0 = 101 325 [Pa]; • atmospheric density, ρ0 = 1,225 [kg/m3]; • temperature, T0 = 288,15 [K]; • speed of sound, a0 = 340,294 [m/s].

The remaining characteristics are calculated using initial values as a basis. By definition, at mean sea level geodetic and geoptential altitudes are the same:

h = H; (2-8) and acceleration due to gravity, g, is equal to the standard acceleration due to gravity, g0:

g = g0. (2-9)

2.4. TEMPERATURE AND VERTICAL TEMPERATURE GRADIENT

According to the temperature variations with altitude, the atmosphere is divided into several layers: troposphere, stratosphere, mesosphere and thermosphere, whose respective boundaries are the tropopause, stratopause and mesopause. For calculating a standard atmosphere, the temperature of each layer is taken as a linear function of geopotential altitude:

T = Tb + βT (H – Hb) (2-10) where point b is the point of lower limit of the layer concerned, βT is the vertical temperature gradient and Tb and Hb the temperature and the geopotential altitude of the lower limit, respectively.

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Table 2-1: Temperatures and vertical gradients ([4], [5])

Geopotential altitude, H, [km]

Temperature, T, [K]

Temp gradient, βT, [K/km]

Layers and boundaries

-5 320,65

-6,5 troposphere

0 288,15

-6.5 troposphere

11 216,65 tropopause

0

20 216,65

1,0 stratosphere

32 228,65

2,8 stratosphere

47 270,65

0,0 stratosphere

51 270,65 stratopause

-2,8 mesosphere

71 214,65

-2,8 mesosphere

80 196,65

2.5. PRESSURE

Combining hydrostatic equation (2-1) with perfect gas law equation (2-2) and taking into account temperature variations given in (2-10), the following solution is obtained for pressure:

Rg

bb

Tb

T

HHT

ppββ

0

)(1−

−+= (2-11)

for βT different from zero and:

−−= )(exp 0

bb HHTR

gpp (2-12)

for βT equal to zero.

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For example, taking into account just troposphere and stratosphere, pressure is calculated as follows:

• below tropopause o βT,< = -6,5 [K/km]; o lower limit is mean sea level, Hb = 0 [m] and Tb = 288,15 [K]; o (2-11) equation is used;

• above tropopause;

o βT,> = 0 [K/km]; o lower limit point is the tropopause, Hb = 11000 [m] and Tb = 216,65 [K]; o (2-12) equation is used.

2.6. DENSITY

The density is calculated from the pressure and the temperature using the perfect gas law (2-2):

TRp

=ρ (2-13)

2.7. SPEED OF SOUND

The speed of sound, a, is the speed at which the pressure waves travel through a fluid and it is given by the expression:

TRa κ= (2-14)

where κ = 1,4 is the adiabatic index of air.

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3. NEW BADA ATMOSPHERE MODEL

The objective of this section is to provide analytical expressions for the atmospheric properties (pressure, temperature, density and speed of sound) as a function of position. These expressions are necessary to obtain the aircraft performances and movement, as both of them depend on the atmospheric properties. Although atmospheric models custom fitted for specific regions and seasons are used for certain applications, the International Standard Atmosphere (ISA) and its variations (referred to as non-ISA standard atmospheres in this document) are widely accepted as standards for computing and evaluating aircraft performances. These are the atmospheric models treated in this section. The development of the new BADA atmosphere model is presented in detail in [2]2

3.1. DEFINITIONS

. The new BADA atmosphere model supports altitudes up to 20 km which is considered to be sufficient for aviation purposes.

The following definitions are necessary to properly comprehend and derive an atmospheric model: i) Speed of sound. The definition is given in section 2.7. It is a function of the fluid properties (air in this case) and its temperature (2-14) ii) A generic atmospheric model is a set of relationships providing the atmospheric pressure, temperature, and density as a function of position, usually defined by its geodetic reference system coordinates:

p, T, ρ = f (λ, φ, h) (3-1)

where λ is the longitude angle, φ the latitude angle and h the geodetic altitude above the surface. Generic atmospheric models usually provide very realistic results for a small geographic area, as they are based on experimental measurements or equations custom fitted to the local atmospheric phenomena.

2 It is worth mentioning that the ISA model describes the atmosphere’s behaviour just for specific initial conditions, for standard

conditions at MSL (2.3). The hypotheses and definitions in the case where initial conditions differ from ISA, with temperature and

pressure deviations at the mean sea level, are not specifically provided by the ISA model. Since BADA APM provides means of

calculating aircraft performances for ISA and non-ISA conditions, the new atmosphere model provides means for that.

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Although (3-1) represents the general case, the influence of latitude and longitude is usually small and can be neglected. The insertion of the relationship between geodetic and geopotential altitudes derived in section 2.2 results in the following expression:

p, T, ρ = f (H) (3-2) iii) ISA atmosphere, defined in section 2, is widely used as the standard for computing and evaluating aircraft performances throughout the world. It provides expressions for the standard atmospheric pressure, temperature, and density as functions of the geopotential altitude H, i.e. as functions of the geopotential pressure altitude HP since they are the same for ISA atmosphere.

p, TISA, ρ = f (HP) (3-3) iv) Standard temperature TISA is the atmospheric temperature that occurs in the ISA atmosphere. It is a function of the geopotential pressure altitude HP. v) Geopotential pressure altitude HP is the geopotential altitude that occurs in the ISA atmospheric conditions. vi) Mean sea level standard conditions are those that occur in the ISA atmosphere at the point where the geopotential pressure altitude HP is zero. They are denoted as T0, p0, ρ0, and a0 with the values defined in section 2.3. vii) Mean sea level conditions are those that occur in a non-ISA atmosphere. They are identified by the sub index MSL and differ from (T0, p0, ρ0, a0) in non-ISA conditions. viii) Non-ISA atmospheres are those that follow the same hypotheses as the ISA atmosphere but differ from it in that one or both of the following parameters is not zero:

1. ΔT. Temperature differential at mean sea level. It is the difference in atmospheric temperature between a given non standard atmosphere and ISA at mean sea level.

2. Δp. Pressure differential at mean sea level. It is the difference in atmospheric pressure at mean sea level between a given atmosphere and ISA.

The values of these two parameters uniquely identify any non ISA atmosphere. Thus, a non ISA atmosphere provides expressions for the atmospheric pressure, temperature, and density as functions of the geopotential altitude H and its two differentials.

p, T, ρ = f (H, ΔT, Δp) (3-4)

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ix) Atmospheric ratios are dimensionless variables containing the ratios between the atmospheric properties at a given point and those found in standard mean sea level conditions.

δ = p / p0 (3-5)

θ = T / T0 (3-6)

σ = ρ / ρ0 (3-7)

α = a / a0 (3-8)

3.2. HYPOTHESES

Any atmospheric model that does not comply with any of below listed hypotheses would belong to the category of generic atmospheres, as described in section 3.1, and not comply with the expressions that appear in section 3.4. i) The atmosphere is composed of air, which is a perfect gas. Its thermodynamic properties

(pressure, temperature, and density) at any point are thus related by the law of perfect gases given in (2-2).

ii) The atmosphere is static in relation to the Earth, so the fluidostatic equilibrium given by (2-1)

must be used. The insertion of expression (2-5) in (2-1) provides the pressure differential in terms of geopotential altitude:

dp = −ρ g0 dH (3-9) iii) The tropopause is the separation between two different layers: the troposphere, which stands

below it, and the stratosphere, which is placed above. Its altitude HP,trop is constant when expressed in terms of geopotential pressure altitude:

HP,trop = 11 000 [m] (3-10)

Note that subindex < denotes values below and equal to the tropopause and subindex > denotes values above the tropopause.

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iv) Temperature changes with altitude according to a given gradient βT, which is constant for each atmospheric layer when expressed in terms of geopotential pressure altitude:

[ ] [ ][ ] [ ]

>≤×−

==−

mHmKmHmK

wheredHdTP

PTPT 11000;/0

11000;/105,6,

3

ββ (3-11)

For more details see Table 2-1. v) The air humidity RH does not affect the value of any other atmospheric property, and hence is

not taken into account.

3.3. RELATIONSHIP BETWEEN GEOPOTENTIAL AND GEOPOTENTIAL PRESSURE ALTITUDES

Although both types of altitudes have been defined in section 3.1, the obtention of the mathematical expression linking them is of particular importance, as the performances of an aircraft are usually provided in terms of geopotential pressure altitude HP, while its movement must be expressed in geodetic altitude h, which is directly linked with the geopotential altitude H per (2-7). The combination of the law of perfect gases (2-2) and the fluidostatic vertical equilibrium (2-1) expressions results in:

dp = − (p/RT) * g0 dH (3-12) In the case of the ISA atmosphere, section 2, and according to the definitions of section 3.1, the atmospheric temperature becomes the standard temperature (T = TISA), and the geopotential altitude turns into the geopotential pressure altitude (H = HP). Inserting these results in the expression above results in:

dp = − (p/RTISA) * g0 dHP (3-13) The ratio between the differentials of both types of altitudes is obtained by dividing expression (3-12) by (3-13):

dH / dHP = T / TISA (3-14) The ratio between incremental changes of geopotential altitude and geopotential pressure altitude is thus the same as that between the atmospheric temperature at that point and the temperature that would occur in the standard atmospheric conditions at the same point.

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3.4. EXPRESSIONS

This section contains the relationships linking the following five variables for any non ISA atmosphere identified by ΔT and Δp as defined in section 3.1. The expressions are also applicable to the case of the standard atmosphere, by replacing both parameters with zeros. These five variables are listed below:

i. Atmospheric pressure p.

ii. Atmospheric temperature T.

iii. Atmospheric standard temperature TISA.

iv. Geopotential pressure altitude HP.

v. Geopotential altitude H. The atmospheric density ρ and the speed of sound a can be easily obtained by using expressions (2-2) and (2-14), respectively. The atmospheric ratios (pressure δ, temperature θ, density σ, and speed of sound α) defined in section 3.1 can then be determined by dividing the atmospheric variables by their values at mean sea level standard conditions. The expressions are the result of the integration of differential equations, so their values at certain points are needed to obtain the complete expressions. These reference points are the following: i. Standard mean sea level (subindex HP = 0). Its definition in section 3.1 includes the values for

the geopotential pressure altitude HP, pressure p, and standard temperature TISA. The temperature differential ΔT sets the value of the real temperature T in non standard atmospheres.

HP,HP = 0 = 0 (3-15)

TISA,HP=0 = T0 (3-16)

pHP=0 = p0 (3-17)

THP=0 = T0 + ΔT (3-18)

HHP=0 = 1/βT,< (T0 − TISA,MSL + ΔT Ln (T0 / TISA,MSL)) (3-19)

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ii. Mean sea level (subindex MSL). Equation (2-8) shows that the values of the geopotential and

geodetic altitudes (H and h) coincide at mean sea level. In order to simplify the expressions, this document assumes that the geopotential altitude at mean sea level is always zero, which repercutes in the atmospheric expressions provided in this section. They should be amended in case very detailed geopotential models are used.

The pressure differential Δp sets the value of the atmospheric pressure p.

HMSL = 0 (3-20)

pMSL = p0 + Δp (3-21)

=

<−

<

10

,

0,

0,

gR

MSL

TMSLP

T

ppTH

β

β (3-22)

TISA,MSL = T0 + βT,< HP,MSL (3-23)

TMSL = T0 + ΔT + βT,< HP,MSL (3-24)

iii. Tropopause (subindex trop). Equation (3-10) sets its geopotential pressure altitude HP. The

other values are obtained throughout this section. According to the definitions of section 3.1, the standard temperature TISA and the geopotential pressure altitude HP are not necessary to define an atmospheric model. However, they are included as they simplify the resulting expressions and facilitate their understanding. i. TISA = f (HP)

TISA,< = T0 + βT,<HP,< TISA,trop = T0 + βT,< HP,trop (3-25) TISA,> = TISA,trop

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ii. p = f (HP)

Rg

PT T

TH

pp<

−<<

<

+=

,

0

0

,,0 1

ββ

Rg

tropPTtrop

T

TH

pp<

−<

+=

,

0

0

,,0 1

ββ (3-26)

( )

−−= >> tropPP

tropISAtrop HH

TRg

pp ,,,

0exp

iii. p = f (TISA)

Rg

ISA T

TT

pp<

−<

<

=

,

0

0

,0

β

Rg

tropISAtrop

T

TT

pp<

=

,

0

0

,0

β (3-27)

tropISAISA TT ,, => , so p> does not directly depend on temperature TISA>.

iv. T = f (HP, ΔT)

T< = T0 + ΔT + βT,< HP,< Ttrop = T0 + ΔT + βT,< HP,trop (3-28) T> = Ttrop

v. T = f (TISA, ΔT)

T = TISA + ΔT (3-29)

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vi. p = f (T, ΔT)

Rg

T

TTTpp

<−

<<

∆−=

,

0

00

β (3-30)

Rg

troptrop

T

TTT

pp<

∆−=

,

0

00

β

T> = Ttrop, so p> does not directly depend on temperature T>. vii. H = f (HP, ΔT, Δp)

+∆+−= <<

<<<

MSLISA

PT

TMSLPP T

HTLnTHHH

,

,,0

,,,

ββ

+∆+−= <

< MSLISA

tropPT

TMSLPtropPtrop T

HTLnTHHH

,

,,0

,,,

ββ

(3-31)

( )tropPPtropPT

tropPTtropP HH

HTHTT

HH ,,,,0

,,0, −

++∆+

+= ><

<> β

β

viii. H = f (TISA, ΔT, Δp)

∆+−= <

<<

<MSLISA

ISAMSLISAISA

T TT

LnTTTH,

,,,

,

∆+−=

< MSLISA

tropISAMSLISAtropISA

Ttrop T

TLnTTTH

,

,,,

,

(3-32)

TISA,> = TISA,trop, so H> does not directly depend on temperature TISA>. ix. H = f (T, ΔT, Δp)

∆−∆+−∆−= <

<<

<MSLISA

MSLISAT T

TTLnTTTTH,

,,

∆−∆+−∆−=

< MSLISA

tropMSLISAtrop

Ttrop T

TTLnTTTTH

,,

,

(3-33)

T> = Ttrop, so H> does not directly depend on temperature T>.

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x. H = f (p, ΔT, Δp)

∆+−

=

<

<

<−

<

<<

MSLISA

gR

MSLISA

gR

T TppT

LnTTppTH

T

T

,

00

,0

0,

0

,

0

,

1

β

β

β

∆+−

=

<

<

< MSLISA

gR

trop

MSLISA

gR

trop

Ttrop T

pp

TLnTT

pp

TH

T

T

,

00

,0

0,

0

,

0

,

1

β

β

β (3-34)

++∆+

−= >

<

<>

trop

tropISA

tropPT

tropPTtrop p

pLng

TRHT

HTTHH

0

,

,,0

,,0

ββ

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4. KEY DIFFERENCES BETWEEN THE OLD AND NEW ATMOSPHERE MODELS

For the standard ISA conditions with no temperature or pressure deviation the old and new models are the same. The differences appear in non-ISA atmosphere conditions due to use of different altitude types (section 2.2 and 3.3) and the way the tropopause altitude is defined. Namely, the old model defines tropopause altitude in terms of the constant tropopause temperature: Ttrop = 216.65 [K] ; (4-1) Below the tropopause the temperature is calculated as a function of geopotential altitude, ISA mean see level temperature (T0) and temperature gradient βT:

T = T0 + βT *H ; (4-2) Figure 4-1 depicts the variation of the tropopause altitude in function of temperature deviation as used by the old model.

T0Ttrop T

H

11.000m

Tropopause level at To+ΔT

Tropopause level at To-ΔT ΔT ΔT

To-ΔT To+ΔT

Tropopause level at To

Figure 4-1: The relationship between tropopause altitude and temperature for the old model

The new model introduces the notion of geopotential pressure altitude and the definition of tropopause is given in terms of the constant tropopause geopotential pressure altitude:

Hptrop = 11000 [m] ; (4-3) and below the tropopause the temperature is calculated as:

T = T0 + βT * Hp ; (4-4)

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as function of geopotential pressure altitude, which differs from geopotential altitude H, and where T0 is ISA mean see level temperature (288,15 [K]). The relationship between geopotential pressure altitude and temperature for the new model is shown in Figure 4-2.

Figure 4-2: The relationship between geopotential pressure altitude and temperature for the new model

In Figure 4-3 the relationship between geoptential altitude and temperature for the new model is given together with tropopause geopotential pressure altitude (dashed line, Hp = 11000 [m]).

Figure 4-3: The relationship between geopotential altitude and temperature for the new model

All subsequent differences between the old and the new BADA atmosphere models are based on the above mentioned basic differences.

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5. IMPACT OF CHANGES ON BADA FAMILY 3

Implementation of the new atmospheric model described in previous sections implies modifications in some of the algorithms of the BADA Aircraft Performance Model family 3 [1]. In principle these modifications are the result of the introduction and implementation of proper relationship between different altitude types: geodetic, geopotential and geopotential pressure described in section 2.2 and 3.3. As such, they can be considered more as clarifications, which would help in reducing ambiguity and alignment with standard definitions, rather then the changes. In line with this, the formulation of the total energy model remains the same, while though a clear distinction is made between the definition of vertical speed and rate-of-climb/descent.

Vertical speed is defined as the variation with time of the aircraft geodetic altitude. The assumption of a standard constant gravity field derives in identical geodetic and geopotential altitudes.

1

dhdV

gV1

mgD)V(T

dtdh TASTASTAS

+

−= (5-1)

The rate-of-climb/descent is defined as the variation with time of the aircraft geopotential pressure altitude Hp. It is the preferred way of presenting the performances of an aircraft as it eliminates possible variations caused by the atmospheric conditions:

1

dhdV

g

V1

mgD)V(T

T

T

dtdH TASTASTASISAp

+

−==ROCD (5-2)

The formulation of energy share factor is modified to take into account proper altitude definitions.

Table 5-1 provides a summary of all the changes in the BADA operations performance model affected by the new atmosphere model.

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Table 5-1: New BADA atmosphere model impact

Change BADA User manual revision 3.7 New BADA atmosphere model impact Formula (3.1-6) 1

2T Mg 2k R 1{M} f

+=γ

1

2T Mg 2k R

1{M} f−

∆−+=

TTTγ

Formula (3.1-7) 1

1211

22T 1M2

1-+1M2

1-+1Mg 2k R 1{M} f

−−−

++=

γγ

γ γγγ 1211

22T 1M2

1-+1M

21-

+1Mg 2k R

1{M} f

−−

+

∆−+=

γ

γ

γ γγγT

TT

Formula (3.2-18) ( )[ ]trans0trans 1T)5.6()3048(.

1000 h θ−⋅⋅

= geopotential pressure altitude must be used, HP,trans

Maximum speed and altitude hMO

geopotential pressure altitude must be used, HP,MO

Maximum speed and altitude Hmax

geopotential pressure altitude must be used, HP,max

Formula (3.5-1) ] )mm (G)CT(Gh, h [ MIN h actmaxwTc,4ISAtmaxMOmax/act −×+−∆+= ×

geopotential pressure altitudes must be used, HPmax, act

Section 3.6.2 Altitude > 15000

geopotential pressure altitude must be used

Section 3.6.2 Altitude < 15000

geopotential pressure altitude must be used

Formula (3.7-1) ( )

+= ×× 2

Tc,3Tc,2

Tc,1ISAclimbmax hCC

h - 1C T gepotential pressure altitude must be used:

( )

+= ××

2PTc,3

Tc,2

PTc,1ISAclimbmax HC

CH - 1C T

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Change BADA User manual revision 3.7 New BADA atmosphere model impact Formula (3.7-2)

( ) Tc,3Tc,1ISAclimbmax C C TTc,2Ch

- 1 +=

× TASV

gepotential pressure altitude must be used:

( ) Tc,3Tc,1ISAclimbmax C C TTc,2C

PH - 1 +=

× TASV

Formula (3.7-3) ( )TASVTc,3

Tc,2Tc,1ISAclimbmax

C

Ch - 1C T +

= ×

gepotential pressure altitude must be used:

( )TASVTc,3

Tc,2

PTc,1ISAclimbmax

C

CH

- 1C T +

= ×

Formula (3.7-9) climbmax highTdes,highdes, T C T ×= The threshold altitude value must be geopotential pressure altitude, HP,des

Section 3.8 h < (0.8*hmax)

Geopotential pressure altitudes must be used.

Formula (3.8-2) } M { f mg

CVD)(T

dtdh redpow,TASclimbmax,

××−= } M { f

mgCVD)(T

T

T-T dtdh redpow,TASclimbmax,

××−∆=

Formula (3.9-4)

=

f4f3min C

h-1 C f geopotential pressure altitude must be used:

=

f4

Pf3min C

H-1 C f

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6. BENEFITS OF IMPLEMENTING THE NEW ATMOSPHERE MODEL

The most evident benefit of implementing the new atmosphere model is ensured consistency between the atmosphere model used by aircraft performance model and the one used by the aircraft manufacturer. From the aircraft performance modelling point of view the major advantages of this consistency are:

1. miss-modelling issues during optimisation of coefficients of an aircraft performance model are avoided

2. improved results in terms of aircraft model accuracy are obtained To this end, an assessment was done during development of the aircraft models for BADA 3.7. All newly developed aircraft models in BADA 3.7 (82) were identified using the new atmosphere model. The aircraft performances in terms of aircraft vertical speed and fuel flow obtained from the BADA 3.7 coefficients together with old and new atmosphere models were compared. This showed improved accuracy for 82% (67 of 82) of aircraft models in BADA 3.7 for non-ISA conditions. The results for ISA conditions remain the same. Accuracy tables for new and old BADA atmosphere models are provided in the Appendix A. By implementing the new atmosphere model, the aircraft trajectory prediction tools would gain the benefits from improved aircraft performance model accuracy in vertical and horizontal plane for off ISA atmosphere conditions.

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7. CONCLUSIONS AND RECOMMENDATIONS

The introduction of the new atmosphere model improves consistency between aircraft performance related applications on the ground and in the air. It also provides a window of opportunity to increase accuracy of the aircraft performance models and simulated or predicted aircraft trajectories. All newly developed aircraft models in BADA 3.7, which were identified using the new BADA atmosphere model, demonstrated the advantages in doing so. The new atmosphere model shall be therefore employed as a standard from BADA 3.8 onwards model developments. It is worth emphasising that the aircraft model coefficients of BADA 3.7 and the future BADA family 3 versions are back compatible with the current (old) atmosphere model described in BADA 3.7 User Manual [1]. The user is given the opportunity to evaluate benefits and decide if and when the upgrade to the new atmosphere model will be done. What is important remembering is that for ISA conditions, the use of both atmosphere models would provide the same results. In the case of non-ISA atmosphere conditions, the use of the new atmosphere model in average should provide the better results. Despite the compatibility of the BADA family 3 coefficients with two atmosphere models, the implementation of the new model is highly recommended. Note that a proper integration of the new BADA atmosphere model requires the implementation of all changes.

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APPENDICES

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APPENDIX A: REVISION 3.7 NON-ISA ACCURACY TABLES

This appendix contains accuracy tables for the new and the old atmosphere models. There are two tables per aircraft model. The first table shows the accuracy of the new BADA atmosphere model and the second the accuracy of the old BADA atmosphere model in respect to non-ISA aircraft reference data. The same aircraft model was used for generation of both tables. The accuracy is provided for non-ISA conditions trajectories only. It is presented in terms of RMS, MEAN, STD, MAX values for both vertical speed and fuel flow. RMS, MEAN, STD and MAX are defined for errors (differences) between computed trajectories and reference trajectories. The results are shown in table format below. The average absolute error is defined as:

n

xerror

n

ii∑

== 1 , (8-1)

and is provided for RMS, MEAN, STD, MAX values for both vertical speed and fuel flow. The accuracy tables are organized per non-ISA conditions trajectories for each aircraft and consist of: • TRJ ID – trajectory identifier; • phase – trajectory type: maximum climb (MCMB), climb (CMB), descent (DES),

cruise (CRZ); • CAS1 – CAS < FL100 – standard CAS below 10000 ft; • CAS2 – CAS > FL100 – standard CAS above 10000 ft; • mach – standard Mach above transition altitude; • aircraft mass – initial mass in kg. For climb the mass at first altitude, for descent the

mass at the top of descent and for cruise starting mass. • temperature deviation – temperature difference from the ISA; • RMS, MEAN, STD and MAX – error values provided for both rate of climb and fuel

flow.

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A.1 A30B

Table A-1: A30B with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 300 300 0.78 105000 10 76.20435 0.82357 76.19989 -192.46938 3.91082 3.22249 2.21587 8.12533

2 MCMB 300 300 0.78 134000 10 49.41873 6.2644 49.02008 -164.4406 3.89941 3.18997 2.24266 7.56626

3 MCMB 300 300 0.78 165000 10 26.99043 3.21503 26.79826 83.58408 3.03597 2.44791 1.79578 8.35394

4 MCMB 300 300 0.78 134000 20 78.26391 1.24388 78.25403 115.06536 4.74393 2.59178 3.97335 12.40786

Average absolute error: 57.719355 2.88672 57.568065 138.88986 3.8975325 2.8630375 2.556915 9.1133475

Table A-2: A30B with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 300 300 0.78 105000 10 119.54191 -62.73505 101.75747 202.10816 1.86655 0.67788 1.73911 5.18011

2 MCMB 300 300 0.78 134000 10 77.79777 -47.31716 61.75418 -121.70394 1.69691 0.96093 1.39861 4.00809

3 MCMB 300 300 0.78 165000 10 46.22768 -40.85935 21.62204 -73.4438 1.20341 0.58294 1.05279 3.16793

4 MCMB 300 300 0.78 134000 20 155.37878 -87.9422 128.09658 229.30352 6.57159 -4.19728 5.05654 11.75089

Average absolute error: 99.736535 59.71344 78.307568 156.63986 2.834615 1.6047575 2.3117625 6.026755

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A.2 A310

Table A-3: A310 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 320 320 0.82 100000 10 224.79198 17.05564 224.14401 903.90365 4.49119 1.72001 4.14878 9.85249

2 MCMB 320 320 0.82 120000 10 172.60968 11.87825 172.20049 739.92614 4.34384 1.66161 4.01348 10.91265

3 MCMB 320 320 0.82 150000 10 154.13417 -14.98967 153.40355 534.76466 4.01088 1.10552 3.85551 9.60829

4 MCMB 320 320 0.8 120000 20 119.64499 1.08214 119.6401 -375.52621 4.57484 2.8852 3.55032 9.99123

Average absolute error: 167.79521 11.251425 167.34704 638.53017 4.3551875 1.843085 3.8920225 10.091165

Table A-4: A310 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 320 320 0.82 100000 10 273.8599 -66.03891 265.7783 797.13301 4.30872 -1.43866 4.06144 -10.02265

2 MCMB 320 320 0.82 120000 10 201.50123 -59.66969 192.46369 655.89152 4.31547 -1.39211 4.08477 9.94284

3 MCMB 320 320 0.82 150000 10 166.67233 -77.99675 147.2962 476.33533 4.50437 -1.59179 4.21373 -9.60599

4 MCMB 320 320 0.8 120000 20 212.00889 -106.216 183.48277 -613.3906 8.37745 -5.7785 6.06553 -12.82801

Average absolute error: 213.51059 77.480338 197.25524 635.68762 5.3765025 2.550265 4.6063675 10.599873

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A.3 A319

Table A-5: A319 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 310 310 0.78 45000 10 88.5208 -8.35072 88.12603 196.05099 2.3971 1.31008 2.00743 -7.26798

2 MCMB 310 310 0.78 60000 10 67.38551 11.63869 66.37279 -245.19984 1.96453 1.36808 1.40987 3.85515

3 MCMB 310 310 0.78 70000 10 59.10487 3.7925 58.98307 -262.44868 1.90248 1.39715 1.29128 3.9287

4 MCMB 310 310 0.78 60000 20 48.22811 2.29922 48.17327 -112.58197 2.36609 2.03278 1.21087 4.64922

Average absolute error: 65.809823 6.5202825 65.41379 204.07037 2.15755 1.5270225 1.4798625 4.9252625

Table A-6: A319 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 310 310 0.78 45000 10 193.52672 -62.66802 183.09919 282.0681 1.75137 -0.30744 1.72417 -7.49027

2 MCMB 310 310 0.78 60000 10 113.78885 -29.39765 109.92579 192.9824 1.16815 -0.25499 1.13998 -2.81994

3 MCMB 310 310 0.78 70000 10 77.61419 -34.25226 69.64729 -194.74738 1.0942 -0.18595 1.07829 2.50973

4 MCMB 310 310 0.78 60000 20 190.06481 -49.88632 183.40117 -289.4474 2.54668 -1.80836 1.79316 -3.76728

Average absolute error: 143.74864 44.051063 136.51836 239.81132 1.6401 0.639185 1.4339 4.146805

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A.4 A320

Table A-7: A320 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 310 310 0.78 47000 10 46.67168 -4.37804 46.46588 -82.65481 1.93196 1.30956 1.42039 3.71515

2 MCMB 310 310 0.78 64000 10 40.94816 10.42329 39.59933 96.62275 1.72519 1.26873 1.16902 3.48115

3 MCMB 310 310 0.78 77000 10 33.57928 0.78789 33.57004 83.85518 1.73129 1.2165 1.23186 4.49652

4 MCMB 310 310 0.78 64000 20 105.35052 8.58227 105.00036 184.11605 2.19858 1.65606 1.44611 4.94074

Average absolute error: 56.63741 6.0428725 56.158903 111.8122 1.896755 1.3627125 1.316845 4.15839

Table A-8: A320 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 310 310 0.78 47000 10 147.49067 -61.46192 134.07435 -216.92184 1.14479 -0.09133 1.14114 2.83449

2 MCMB 310 310 0.78 64000 10 99.35963 -35.15458 92.93273 158.53496 0.88136 -0.03473 0.88068 2.27944

3 MCMB 310 310 0.78 77000 10 80.112 -41.52056 68.51259 127.2101 1.0904 0.01935 1.09023 4.38028

4 MCMB 310 310 0.78 64000 20 228.96575 -73.05499 216.99835 338.27185 2.35083 -1.92248 1.35295 -3.83261

Average absolute error: 138.98201 52.798013 128.12951 210.23469 1.366845 0.5169725 1.11625 3.331705

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A.5 A321

Table A-9: A321 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 300 300 0.78 55000 10 50.26152 -8.28923 49.57327 139.81497 1.92257 1.36476 1.35415 5.64382

2 MCMB 300 300 0.78 72000 10 38.67585 12.4243 36.62592 -101.42555 1.85664 1.38463 1.23689 5.48562

3 MCMB 300 300 0.78 83000 10 24.35397 6.6158 23.43815 -53.83678 1.87498 1.431 1.21153 3.88629

4 MCMB 300 300 0.78 72000 20 58.40468 6.65904 58.02382 -121.17755 2.22754 1.9836 1.01353 4.90798

Average absolute error: 42.924005 8.4970925 41.91529 104.06371 1.9704325 1.5409975 1.204025 4.9809275

Table A-10: A321 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 300 300 0.78 55000 10 139.61048 -72.66357 119.21028 -200.96869 1.58752 -0.2028 1.57451 5.23182

2 MCMB 300 300 0.78 72000 10 90.88107 -36.94597 83.03231 -137.53955 1.48485 -0.15199 1.47705 4.99143

3 MCMB 300 300 0.78 83000 10 71.20036 -37.60137 60.46179 -115.71843 1.46053 -0.0363 1.46008 3.56347

4 MCMB 300 300 0.78 72000 20 176.50936 -78.25177 158.21572 -331.3021 3.21799 -2.20418 2.34459 -5.15615

Average absolute error: 119.55032 56.36567 105.23003 196.38219 1.9377225 0.6488175 1.7140575 4.7357175

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A.6 A332

Table A-11: A332 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 330 330 0.82 140000 10 67.29547 0.31642 67.29472 133.74573 4.55323 2.71063 3.65847 9.93796

2 MCMB 330 330 0.82 190000 10 45.1548 11.32462 43.71166 -72.80915 4.33392 2.62696 3.44702 10.73642

3 MCMB 330 330 0.82 230000 10 53.31667 -1.72277 53.28883 -178.00609 4.05804 2.15487 3.43864 11.2389

4 MCMB 330 330 0.82 190000 20 60.93093 5.68607 60.66504 126.35944 4.58336 3.20804 3.27348 11.07944

Average absolute error: 56.674468 4.76247 56.240063 127.7301 4.3821375 2.675125 3.4544025 10.74818

Table A-12: A332 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 330 330 0.82 140000 10 137.63716 -58.9172 124.38951 -291.09278 3.4056 -2.27387 2.53528 -9.27856

2 MCMB 330 330 0.82 190000 10 75.77627 -33.24081 68.09619 -178.44041 3.2752 -2.33403 2.29766 -6.85432

3 MCMB 330 330 0.82 230000 10 58.66099 -40.48214 42.4536 -146.61383 3.55253 -2.5716 2.45099 -10.71397

4 MCMB 330 330 0.82 190000 20 160.45355 -56.35905 150.22982 -319.29331 7.92737 -7.05349 3.61822 -13.38961

Average absolute error: 108.13199 47.2498 96.29228 233.86008 4.540175 3.5582475 2.7255375 10.059115

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A.7 A333

Table A-13: A333 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 330 330 0.82 150000 10 41.9702 6.5192 41.4608 -134.24151 3.70702 2.67527 2.56611 9.20361

2 MCMB 330 330 0.82 174000 10 32.66506 4.71403 32.32312 -106.97151 3.32927 2.84244 1.73337 8.98574

3 MCMB 330 330 0.82 212000 10 35.5946 -7.14831 34.86943 -84.82146 3.09377 2.48612 1.84136 6.65452

4 MCMB 330 330 0.82 174000 20 54.13243 0.62805 54.12879 -126.75976 4.30725 3.26914 2.80447 8.78489

Average absolute error: 41.090573 4.7523975 40.695535 113.19856 3.6093275 2.8182425 2.2363275 8.40719

Table A-14: A333 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 330 330 0.82 150000 10 109.7987 -40.29609 102.13706 -282.62088 3.1953 -1.51095 2.81549 -6.62184

2 MCMB 330 330 0.82 174000 10 84.25889 -34.60776 76.82358 -232.89709 2.76376 -1.3513 2.41088 -4.82731

3 MCMB 330 330 0.82 212000 10 65.06836 -45.129 46.87499 -184.73982 2.78964 -1.31739 2.45898 -4.67775

4 MCMB 330 330 0.82 174000 20 140.21772 -65.96162 123.73388 -336.81198 9.75014 -6.29548 7.44528 -17.45177

Average absolute error: 99.835918 46.498618 87.392378 259.26744 4.62471 2.61878 3.7826575 8.3946675

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A.8 A343

Table A-15: A343 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 300 300 0.8 150000 10 56.16694 -7.2836 55.69267 -138.50052 4.33907 3.21468 2.91434 10.89239

2 MCMB 300 300 0.8 180000 10 58.4347 7.79645 57.91226 -107.31083 4.89724 3.40497 3.51982 18.31705

3 MCMB 300 300 0.8 257000 10 40.08637 4.5003 39.83295 -95.79377 4.81282 3.36515 3.4408 14.28775

4 MCMB 300 300 0.8 180000 20 75.15077 5.02706 74.98245 -152.18101 4.95727 3.68398 3.31705 13.11832

Average absolute error: 57.459695 6.1518525 57.105083 123.44653 4.7516 3.417195 3.2980025 14.153878

Table A-16: A343 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 300 300 0.8 150000 10 125.05068 -71.50511 102.58992 -260.44445 3.6837 -0.49686 3.65004 10.22471

2 MCMB 300 300 0.8 180000 10 95.20316 -45.99713 83.3541 -200.97533 4.35826 -0.31569 4.34682 17.86725

3 MCMB 300 300 0.8 257000 10 59.19355 -39.80208 43.81404 -124.52854 4.01533 0.50404 3.98357 13.83794

4 MCMB 300 300 0.8 180000 20 188.77946 -87.85722 167.08917 -315.08836 8.83946 -5.93938 6.54674 -13.11377

Average absolute error: 117.05671 61.290385 99.211808 225.25917 5.2241875 1.8139925 4.6317925 13.760918

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A.9 A346

Table A-17: A346 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 310 310 0.81 185000 10 88.0114 -14.8338 86.75233 233.9129 6.75941 4.3977 5.13321 14.9169

2 MCMB 310 310 0.81 255000 10 76.91113 13.03621 75.79828 191.7457 6.67366 4.23743 5.15577 17.34114

3 MCMB 310 310 0.81 305000 10 54.44364 19.85789 50.69294 122.8235 6.93679 4.44584 5.32481 16.9752

4 MCMB 310 310 0.81 365000 10 28.78084 4.07078 28.4915 -48.8547 5.6145 3.28697 4.55175 18.92062

5 MCMB 310 310 0.81 185000 20 76.81451 -22.0384 73.58518 193.3141 6.26788 4.8186 4.00841 16.20724

6 MCMB 310 310 0.81 255000 20 58.17567 16.66087 55.73889 163.1037 6.26252 5.07172 3.67381 15.63906

7 MCMB 310 310 0.81 305000 20 44.38608 19.83907 39.70561 101.9382 6.21675 5.05818 3.61425 12.21423

8 MCMB 310 310 0.81 365000 20 26.33466 -1.46226 26.29403 -48.7842 6.29579 4.86117 4.00075 15.87054

Average absolute error: 56.732241 13.97491 54.632345 138.05963 6.3784125 4.5222013 4.432845 16.010616

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 41

Table A-18: A346 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 310 310 0.81 185000 10 170.2677 -110.23 129.7709 -241.495 4.31995 -0.35633 4.30523 -8.17905

2 MCMB 310 310 0.81 255000 10 112.2095 -55.7379 97.38718 182.0372 4.35107 -0.49963 4.32229 8.87031

3 MCMB 310 310 0.81 305000 10 85.27111 -39.9791 75.3182 -148.654 4.46665 0.05914 4.46626 9.46821

4 MCMB 310 310 0.81 365000 10 68.24087 -45.2738 51.05974 -132.449 4.09621 -0.58394 4.05437 10.44979

5 MCMB 310 310 0.81 185000 20 239.3581 -152.483 184.5026 -348.252 16.56414 -11.9277 11.49349 -32.7642

6 MCMB 310 310 0.81 255000 20 155.2411 -83.6547 130.7734 -241.966 15.03017 -10.7037 10.55159 -24.7851

7 MCMB 310 310 0.81 305000 20 122.4758 -67.9801 101.8775 -203.879 13.64547 -9.63186 9.66572 -20.5265

8 MCMB 310 310 0.81 365000 20 98.55734 -80.2434 57.22369 -172.673 12.92351 -7.93736 10.1988 -20.2645

Average absolute error: 131.45269 79.44775 103.48915 208.92565 9.4246463 5.2124575 7.3822188 16.913458

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 42

A.10 A388

Table A-19: A388 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 310 310 0.83 560000 10 29.54 -10.09 27.77 -57.32 8.91 6.6 5.97 25.28

2 MCMB 320 320 0.85 326000 10 88.26 29.44 83.2 221.28 12.06 6.32 10.27 25.22

3 MCMB 320 320 0.85 482000 10 39.29 16.24 35.78 -107.25 11.28 4.74 10.23 28.64

4 MCMB 320 320 0.85 560000 10 31.91 -20.23 24.68 -95.65 9.01 3.49 8.3 31.36

5 MCMB 320 320 0.85 326000 20 124.18 15.95 123.15 275.11 8.47 3.69 7.63 19.09

6 MCMB 320 320 0.85 482000 20 67.06 8.38 66.53 -153.41 8.01 2.34 7.66 24.97

7 MCMB 320 320 NaN 560000 20 48.74 -33.68 35.23 -135.67 5.3 -0.72 5.25 -18.98

8 MCMB 310 310 0.83 326000 10 77.72 45.3 63.15 194.25 10.75 7.69 7.51 19.98

9 MCMB 310 310 0.83 482000 10 41.29 27.22 31.05 72.69 10.66 7.03 8.01 -24.41

10 MCMB 310 310 0.83 482000 20 62.04 25.53 56.55 139.13 7.3 4.88 5.42 20.68

Average absolute error: 61.003 23.206 54.709 145.176 9.175 4.75 7.625 23.861

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 43

Table A-20: A388 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 310 310 0.83 560000 10 66.84 -61.37 26.48 -149.97 5.54 0.34 5.53 13.71

2 MCMB 320 320 0.85 326000 10 160.81 -69.98 144.78 -367.09 7.13 -2.63 6.63 -19.21

3 MCMB 320 320 0.85 482000 10 81.33 -54.92 59.99 -219.65 7.84 -3.5 7.02 -24.21

4 MCMB 320 320 0.85 560000 10 81.37 -73.85 34.16 -187.83 6.55 -3.95 5.22 -13.62

5 MCMB 320 320 0.85 326000 20 289.37 -130.39 258.32 -550.78 22.85 -20.64 9.8 -45.05

6 MCMB 320 320 0.85 482000 20 166.86 -86.61 142.62 -336.77 20.83 -19.03 8.45 -32.05

7 MCMB 320 320 NaN 560000 20 142.35 -122.27 72.9 -284.5 20.76 -18.95 8.48 -30.46

8 MCMB 310 310 0.83 326000 10 234.4 5.18 234.34 923.66 6.21 -0.22 6.21 15.78

9 MCMB 310 310 0.83 482000 10 118.69 -9.68 118.3 444.44 6.73 0.06 6.73 -24.85

10 MCMB 310 310 0.83 482000 20 173.41 -48.06 166.62 385.66 19.22 -16.65 9.6 -28.46

Average absolute error: 151.543 66.231 125.851 385.035 12.366 8.597 7.367 24.74

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 44

A.11 AT43

Table A-21: AT43 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 160 160 0.45 11000 10 117.59977 -26.2455 114.63368 -266.72 0.49485 0.11917 0.48028 1.49198

2 MCMB 160 160 0.45 15000 10 71.84908 7.61884 71.44399 139.8924 0.43381 0.116 0.41801 1.05722

3 MCMB 160 160 0.45 17000 10 57.64272 16.46507 55.24115 122.56362 0.36053 0.1733 0.31615 0.87146

4 MCMB 160 160 0.45 15000 20 82.55864 -8.04312 82.16592 -138.81523 0.55758 0.24671 0.50003 1.47728

Average absolute error: 82.412553 14.593133 80.871185 166.99781 0.4616925 0.163795 0.4286175 1.224485

Table A-22: AT43 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 160 160 0.45 11000 10 145.17098 -99.07495 106.10734 -317.5546 0.52665 -0.01471 0.52645 1.47465

2 MCMB 160 160 0.45 15000 10 78.83633 -41.83243 66.82226 -167.03905 0.454 -0.00897 0.45391 0.95859

3 MCMB 160 160 0.45 17000 10 58.17776 -25.09394 52.48758 -115.42758 0.35699 0.05747 0.35234 0.77283

4 MCMB 160 160 0.45 15000 20 115.79729 -93.1295 68.81794 -200.86577 0.59127 0.03055 0.59048 1.41294

Average absolute error: 99.49559 64.782705 73.55878 200.22175 0.4822275 0.027925 0.480795 1.1547525

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 45

A.12 AT45

Table A-23: AT45 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 160 160 NaN 14000 10 37.46371 8.23815 36.54671 73.76396 0.46551 0.12871 0.44737 -1.48808

2 MCMB 160 160 NaN 16500 10 29.68333 0.52229 29.67873 53.86687 0.35235 0.14522 0.32103 -0.95898

3 MCMB 160 160 NaN 18000 10 26.93033 -5.58727 26.34435 -46.82343 0.3623 0.20801 0.29663 0.89287

4 MCMB 160 160 NaN 16500 20 36.01004 3.90388 35.7978 54.64988 0.56803 0.49389 0.28061 1.18455

Average absolute error: 32.521853 4.5628975 32.091898 57.276035 0.4370475 0.2439575 0.33641 1.13112

Table A-24: AT45 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 160 160 NaN 14000 10 64.5072 -47.24974 43.91629 -124.62031 0.44217 -0.08003 0.43487 -1.51905

2 MCMB 160 160 NaN 16500 10 57.76128 -44.06685 37.34271 -109.40088 0.31849 -0.05803 0.31315 -0.98995

3 MCMB 160 160 NaN 18000 10 58.19235 -46.29893 35.25278 -105.78955 0.32554 0.01632 0.32514 0.8619

4 MCMB 160 160 NaN 16500 20 91.90725 -72.68775 56.24441 -158.51383 0.3444 0.14019 0.31457 1.12807

Average absolute error: 68.09202 52.575818 43.189048 124.58114 0.35765 0.0736425 0.3469325 1.1247425

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 46

A.13 AT72

Table A-25: AT72 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 170 170 0.45 14000 10 32.979 -12.34921 30.57959 -89.69435 0.47449 0.14362 0.45223 1.83331

2 MCMB 170 170 0.45 19000 10 17.36383 9.85109 14.29891 37.94766 0.31924 0.0521 0.31496 -0.7235

3 MCMB 170 170 0.45 21500 10 16.24029 10.14104 12.68488 33.85854 0.24808 0.05023 0.24294 -0.55903

4 MCMB 170 170 0.45 19000 20 16.95498 1.86244 16.85238 28.75237 0.55926 0.51159 0.22594 0.84081

Average absolute error: 20.884525 8.550945 18.60394 47.56323 0.4002675 0.189385 0.3090175 0.9891625

Table A-26: AT72 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 170 170 0.45 14000 10 78.2825 -73.22915 27.67021 -120.81156 0.48294 -0.09257 0.47398 1.80034

2 MCMB 170 170 0.45 19000 10 39.06464 -33.85465 19.49124 -58.99761 0.32805 -0.15528 0.28897 -0.75648

3 MCMB 170 170 0.45 21500 10 32.67241 -27.15942 18.16184 -49.33063 0.25324 -0.14169 0.20988 -0.592

4 MCMB 170 170 0.45 19000 20 75.83501 -70.2598 28.53961 -101.60212 0.2951 0.15938 0.24835 0.68474

Average absolute error: 56.46364 51.125755 23.465725 82.68548 0.3398325 0.13723 0.305295 0.95839

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 47

A.14 ATP

Table A-27: ATP with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 160 160 0.34 15992 10 83.06404 -11.5739 82.25376 -239.92646 2.71261 0.05313 2.71208 9.17641

2 MCMB 160 160 0.34 20000 10 73.59226 16.30844 71.76249 133.75385 2.31667 0.45781 2.27099 7.60793

3 MCMB 160 160 0.34 23000 10 42.08881 -4.08099 41.8905 64.041 2.28223 0.52108 2.22195 7.47281

4 MCMB 160 160 0.34 20000 20 56.82539 -4.38093 56.65626 102.37309 1.75691 0.4486 1.69867 5.48057

Average absolute error: 63.892625 9.086065 63.140753 135.0236 2.267105 0.370155 2.2259225 7.43443

Table A-28: ATP with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 160 160 0.34 15992 10 98.52119 -49.02535 85.45724 -301.48739 2.6309 -0.14578 2.62686 8.7596

2 MCMB 160 160 0.34 20000 10 60.91988 -13.99762 59.28995 -93.1372 2.23419 0.27732 2.21691 7.21528

3 MCMB 160 160 0.34 23000 10 51.87481 -30.81836 41.72798 -82.74586 2.2005 0.37048 2.16909 7.11966

4 MCMB 160 160 0.34 20000 20 73.12916 -56.81416 46.04373 -113.98422 1.67193 0.10782 1.66845 4.80085

Average absolute error: 71.11126 37.663873 58.129725 147.83867 2.18438 0.22535 2.1703275 6.9738475

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 48

A.15 B462

Table A-29: B462 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 250 0.6 42000 10 281.67891 36.82745 279.26108 410.94946 10.69114 3.01403 10.25749 23.11606

2 MCMB 250 250 0.6 36000 10 116.80915 -17.74019 115.45416 -239.36244 8.43769 0.82208 8.39754 16.74571

3 MCMB 250 250 0.6 30000 10 86.40431 -50.8521 69.85534 -165.96035 6.91777 -0.1943 6.91504 -14.94555

4 MCMB 250 250 0.6 36000 20 232.33125 34.23133 229.79561 349.0208 8.28121 2.61359 7.85796 22.10154

Average absolute error: 179.30591 34.912768 173.59155 291.32326 8.5819525 1.661 8.3570075 19.227215

Table A-30: B462 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 250 0.6 42000 10 245.42969 22.24325 244.41966 -354.54165 10.655 2.5595 10.34302 22.93108

2 MCMB 250 250 0.6 36000 10 97.72122 -46.03473 86.19884 -204.58879 8.51484 -0.05899 8.51464 16.56073

3 MCMB 250 250 0.6 30000 10 120.08812 -93.33122 75.56745 -173.32664 6.8928 -1.15588 6.79519 -15.54048

4 MCMB 250 250 0.6 36000 20 167.28158 4.99176 167.20709 235.21124 8.44457 1.30096 8.34375 21.75767

Average absolute error: 157.63015 41.65024 143.34826 241.91708 8.6268025 1.2688325 8.49915 19.19749

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 49

A.16 B712

Table A-31: B712 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 275 275 0.72 30600 10 92.68543 9.21728 92.22597 -256.05369 0.89086 0.70535 0.54415 2.74132

2 MCMB 275 275 0.72 46000 10 45.65726 4.80622 45.40359 -96.09567 0.87899 0.69453 0.53875 2.78811

3 MCMB 275 275 0.72 52600 10 58.15721 -15.50345 56.05269 -123.94438 0.78024 0.62801 0.463 2.50034

4 MCMB 275 275 0.72 46000 20 67.9936 1.97888 67.9648 -170.38804 1.73643 1.57007 0.74166 4.18674

Average absolute error: 66.123375 7.8764575 65.411763 161.62045 1.07163 0.89949 0.57189 3.0541275

Table A-32: B712 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 275 275 0.72 30600 10 165.82906 -111.52119 122.72856 -450.55998 0.67305 -0.19591 0.64391 -1.25328

2 MCMB 275 275 0.72 46000 10 82.00863 -68.62484 44.90042 -218.64253 0.66941 -0.20596 0.63694 -1.24656

3 MCMB 275 275 0.72 52600 10 86.90761 -77.10328 40.10009 -172.94611 0.67752 -0.19293 0.64947 -1.26324

4 MCMB 275 275 0.72 46000 20 152.3034 -105.61919 109.73109 -361.96255 2.50821 -1.67612 1.86594 -4.51598

Average absolute error: 121.76218 90.717125 79.36504 301.02779 1.1320475 0.56773 0.949065 2.069765

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 50

A.17 B722

Table A-33: B722 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 300 300 0.78 74000 10 186.29828 16.76873 185.54207 -471.13226 32.05183 -2.66533 31.94082 110.85185

2 MCMB 280 280 0.75 74000 10 180.24613 -22.90425 178.78496 -454.53938 29.57463 -1.89369 29.51394 99.49412

3 MCMB 280 280 0.75 58000 10 182.28013 4.66408 182.22045 420.86211 30.0569 0.66548 30.04953 67.20049

4 MCMB 280 280 0.75 86000 10 96.40853 55.13753 79.08513 300.16638 17.21574 1.2487 17.1704 42.34808

Average absolute error: 161.30827 24.868648 156.40815 411.67503 27.224775 1.6183 27.168673 79.973635

Table A-34: B722 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 300 300 0.78 74000 10 164.98491 2.1074 164.97145 -546.04133 32.20487 -4.05547 31.94851 106.60596

2 MCMB 280 280 0.75 74000 10 167.59867 -44.89646 161.47328 -528.98069 28.68853 -2.40088 28.58789 95.37594

3 MCMB 280 280 0.75 58000 10 193.45278 -28.6273 191.32291 -503.21851 29.70724 -1.1713 29.68414 61.1658

4 MCMB 280 280 0.75 86000 10 84.46957 26.76144 80.11825 236.21581 17.25311 -1.19711 17.21153 38.08257

Average absolute error: 152.62648 25.59815 149.47147 453.61409 26.963438 2.20619 26.858018 75.307568

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 51

A.18 B732

Table A-35: B732 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 280 280 0.7 27200 10 146.14394 -4.21793 146.08306 248.30018 1.27638 0.57178 1.14115 2.81501

2 MCMB 280 280 0.7 44800 10 70.24884 17.00016 68.1608 140.55679 1.26325 0.56349 1.13061 2.82247

3 MCMB 280 280 0.7 52300 10 48.15761 3.70768 48.01467 -99.80449 1.22645 0.51805 1.11166 2.88923

4 MCMB 280 280 0.7 44800 20 98.67614 12.96134 97.82119 204.91627 2.1493 1.54999 1.48897 4.61779

Average absolute error: 90.806633 9.4717775 90.01993 173.39443 1.478845 0.8008275 1.2180975 3.286125

Table A-36: B732 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 280 280 0.7 27200 10 233.34079 -108.37276 206.64769 -331.68327 1.60932 -1.33455 0.89937 -2.3618

2 MCMB 280 280 0.7 44800 10 106.93023 -40.52194 98.95477 -155.58282 1.6162 -1.34359 0.89826 -2.33787

3 MCMB 280 280 0.7 52300 10 79.47478 -43.19909 66.70891 -121.98402 1.63304 -1.34884 0.92057 -2.28701

4 MCMB 280 280 0.7 44800 20 176.57979 -69.78584 162.20468 224.5599 2.86389 -1.93667 2.10978 -4.04483

Average absolute error: 149.0814 65.469908 133.62901 208.4525 1.9306125 1.4909125 1.206995 2.7578775

Page 68: EUROCONTROL · 2019-02-18 · The information contained in this document may not be modified without prior written permission from EUROCONTROL. EUROCONTROL makes no warranty, either

EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 52

A.19 B733

Table A-37: B733 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 280 280 0.74 62800 10 49.70533 5.23594 49.42878 -206.03656 1.29448 0.9592 0.86925 3.01687

2 MCMB 280 280 0.74 32900 10 54.97828 -15.62356 52.71163 -247.80163 1.33794 1.00207 0.88653 2.80898

3 MCMB 280 280 0.74 52500 10 33.36587 20.50649 26.32043 -85.07537 1.31841 0.99178 0.86866 2.77378

4 MCMB 280 280 0.74 52500 20 50.71412 5.45791 50.41957 -129.00122 1.77685 1.59725 0.77844 3.7325

Average absolute error: 47.1909 11.705975 44.720103 166.9787 1.43192 1.137575 0.85072 3.0830325

Table A-38: B733 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 280 280 0.74 62800 10 70.90915 -57.45446 41.5583 -207.58448 1.26861 -0.58126 1.12761 -2.14969

2 MCMB 280 280 0.74 32900 10 189.67921 -152.36045 112.98006 -493.56266 1.26384 -0.56478 1.13063 -2.17445

3 MCMB 280 280 0.74 52500 10 75.84838 -59.13808 47.49384 -181.55194 1.25794 -0.57815 1.11721 -2.13604

4 MCMB 280 280 0.74 52500 20 184.86431 -129.92161 131.51117 -383.24026 2.71781 -1.98619 1.85514 -3.86103

Average absolute error: 130.32526 99.71865 83.385843 316.48484 1.62705 0.927595 1.3076475 2.5803025

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 53

A.20 B734

Table A-39: B734 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 280 0.74 45000 10 53.36333 -11.01166 52.21483 -118.08842 1.43399 1.09869 0.92152 2.63165

2 MCMB 250 280 0.74 58000 10 44.23306 9.32929 43.23804 -150.70837 1.39204 1.06743 0.89351 2.59293

3 MCMB 250 280 0.74 68000 10 46.88433 7.29504 46.31331 -196.37485 1.39887 1.03255 0.94376 3.52865

4 MCMB 250 280 0.74 58000 20 54.07218 3.28949 53.97203 101.68833 1.92976 1.36726 1.36183 4.62027

Average absolute error: 49.638225 7.73137 48.934553 141.71499 1.538665 1.1414825 1.030155 3.343375

Table A-40: B734 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 280 0.74 45000 10 146.57009 -117.13828 88.0989 -300.64235 1.22838 -0.5735 1.08628 1.93416

2 MCMB 250 280 0.74 58000 10 87.34743 -67.56634 55.3567 -163.79762 1.21286 -0.6072 1.04992 -1.76743

3 MCMB 250 280 0.74 68000 10 72.18654 -55.02721 46.72154 -204.92062 1.22937 -0.57488 1.08668 -1.77742

4 MCMB 250 280 0.74 58000 20 172.54111 -126.862 116.94643 -274.33473 3.44494 -2.4949 2.37552 -4.87154

Average absolute error: 119.66129 91.648458 76.780893 235.92383 1.7788875 1.06262 1.3996 2.5876375

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 54

A.21 B735

Table A-41: B735 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 280 0.74 40000 10 58.06708 -29.09794 50.25034 -130.19964 1.62774 -1.42088 0.79412 -2.49911

2 MCMB 250 280 0.74 52000 10 35.99471 17.95789 31.19508 70.48069 1.62659 -1.42269 0.78852 -2.55144

3 MCMB 250 280 0.74 60000 10 39.74343 24.10683 31.59748 -85.32111 1.65799 -1.45859 0.78832 -2.54358

4 MCMB 250 280 0.74 52000 20 48.25532 3.1198 48.15437 -98.25759 0.80533 -0.30906 0.74367 -1.35337

Average absolute error: 45.515135 18.570615 40.299318 96.064758 1.4294125 1.152805 0.7786575 2.236875

Table A-42: B735 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 280 0.74 40000 10 148.73551 -125.14725 80.37672 -297.41211 3.49617 -3.25604 1.27335 -4.57286

2 MCMB 250 280 0.74 52000 10 71.82182 -51.90467 49.6415 -149.37054 3.50117 -3.25815 1.28166 -4.55306

3 MCMB 250 280 0.74 60000 10 49.30182 -34.17331 35.53667 -104.90718 3.51811 -3.26552 1.30899 -4.59462

4 MCMB 250 280 0.74 52000 20 160.76552 -114.53038 112.81997 -291.3359 4.20762 -3.73861 1.93052 -5.57399

Average absolute error: 107.65617 81.438903 69.593715 210.75643 3.6807675 3.37958 1.44863 4.8236325

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 55

A.22 B736

Table A-43: B736 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 280 280 0.78 44000 10 166.88334 -15.51476 166.16059 -397.29963 3.11988 1.08496 2.92515 7.14037

2 MCMB 280 280 0.78 55000 10 134.80694 11.59318 134.30752 -291.46305 3.14361 1.08749 2.94951 7.5341

3 MCMB 280 280 0.78 65000 10 124.65021 13.93875 123.86842 -235.74428 3.14455 1.05434 2.96252 7.22052

4 MCMB 280 280 0.78 55000 20 163.78075 6.06803 163.66831 -348.8001 3.1393 1.1032 2.93908 6.88177

Average absolute error: 147.53031 11.77868 147.00121 318.32677 3.136835 1.0824975 2.944065 7.19419

Table A-44: B736 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 280 280 0.78 44000 10 198.79771 -92.95211 175.7283 -500.38382 2.9129 -0.21052 2.90529 7.01538

2 MCMB 280 280 0.78 55000 10 147.83341 -49.66678 139.24053 -370.64647 2.94368 -0.20882 2.93626 7.40911

3 MCMB 280 280 0.78 65000 10 127.46034 -38.30891 121.56712 -299.18058 2.9577 -0.20291 2.95073 7.09553

4 MCMB 280 280 0.78 55000 20 226.2222 -91.89514 206.71663 -469.42716 4.49942 -2.70862 3.59279 -7.28424

Average absolute error: 175.07842 68.205735 160.81315 409.90951 3.328425 0.8327175 3.0962675 7.201065

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 56

A.23 B737

Table A-45: B737 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 280 0.78 46000 10 55.47373 -16.77991 52.87503 -146.27875 1.76927 1.36797 1.12204 3.72585

2 MCMB 250 280 0.78 60000 10 50.9593 9.49367 50.06716 -184.13643 1.73865 1.34104 1.10657 3.74613

3 MCMB 250 280 0.78 70000 10 39.52865 12.08728 37.63524 -171.09472 1.67602 1.25512 1.11073 4.19219

4 MCMB 250 280 0.78 60000 20 69.29865 5.17368 69.10525 155.82205 1.55649 0.90066 1.26943 3.42113

Average absolute error: 53.815083 10.883635 52.42067 164.33299 1.6851075 1.2161975 1.1521925 3.771325

Table A-46: B737 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 280 0.78 46000 10 156.94783 -106.09249 115.659 -337.16369 1.26672 -0.36432 1.21319 2.07696

2 MCMB 250 280 0.78 60000 10 90.35251 -57.46044 69.72714 -180.74319 1.24698 -0.39187 1.18381 -1.94855

3 MCMB 250 280 0.78 70000 10 67.79277 -49.38765 46.4405 -142.63466 1.31316 -0.38594 1.25517 -1.9768

4 MCMB 250 280 0.78 60000 20 194.32296 -110.99785 159.50201 -345.27176 4.20428 -3.46648 2.37897 -6.03313

Average absolute error: 127.35402 80.984608 97.832163 251.45333 2.007785 1.1521525 1.507785 3.00886

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 57

A.24 B738

Table A-47: B738 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 280 280 0.78 41400 10 55.94426 -19.09017 52.58636 -182.70583 1.78147 1.41252 1.08555 3.97844

2 MCMB 280 280 0.78 65300 10 50.08179 15.36714 47.66589 -191.42687 1.72422 1.36174 1.05764 4.00472

3 MCMB 280 280 0.78 78300 10 38.26794 16.00913 34.75835 -135.56446 1.56471 1.19945 1.00481 4.27823

4 MCMB 280 280 0.78 65300 20 60.79456 5.86525 60.51097 144.32068 1.43485 0.75007 1.22318 3.82233

Average absolute error: 51.272138 14.082923 48.880393 163.50446 1.6263125 1.180945 1.092795 4.02093

Table A-48: B738 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 280 280 0.78 41400 10 177.63578 -112.57314 137.41091 -395.4365 1.21521 -0.32289 1.17153 2.2085

2 MCMB 280 280 0.78 65300 10 75.47864 -43.81388 61.4603 -147.28343 1.23115 -0.34367 1.1822 -1.92322

3 MCMB 280 280 0.78 78300 10 45.74907 -37.98275 25.50074 -91.65501 1.31243 -0.35544 1.26338 2.00643

4 MCMB 280 280 0.78 65300 20 177.71662 -102.92002 144.88156 -310.58356 4.08185 -3.3347 2.354 -6.15059

Average absolute error: 119.14503 74.322448 92.313378 236.23963 1.96016 1.089175 1.4927775 3.072185

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 58

A.25 B742

Table A-49: B742 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 340 340 0.82 172600 10 154.00358 -107.2066 110.56152 -221.29807 7.08756 5.66333 4.26148 14.99957

2 MCMB 340 340 0.82 255800 10 116.72029 92.10555 71.69515 188.76107 7.46264 6.29668 4.00535 14.24814

3 MCMB 340 340 0.82 356000 10 122.09193 116.94591 35.07268 182.30843 7.86765 6.56917 4.32965 15.20654

4 MCMB 340 340 0.82 255800 20 72.63825 2.20325 72.60483 191.48626 3.99154 2.25716 3.29206 9.61111

Average absolute error: 116.36351 79.615328 72.483545 195.96346 6.6023475 5.196585 3.972135 13.51634

Table A-50: B742 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 340 340 0.82 172600 10 249.29625 -185.70957 166.3147 -366.49531 6.90881 -1.38678 6.7682 13.50212

2 MCMB 340 340 0.82 255800 10 77.95452 25.79958 73.56146 -181.82289 6.18846 -0.26224 6.18291 12.7507

3 MCMB 340 340 0.82 356000 10 73.45446 67.09193 29.90368 126.29349 6.07716 1.11235 5.97449 13.02362

4 MCMB 340 340 0.82 255800 20 181.03806 -103.70685 148.39026 -313.75506 17.29899 -14.42849 9.54324 -30.44728

Average absolute error: 145.43582 95.576983 104.54253 247.09169 9.118355 4.297465 7.11721 17.43093

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 59

A.26 B743

Table A-51: B743 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 330 0.84 210000 10 126.74078 -104.45779 71.776 -225.4857 6.1324 5.35162 2.99441 14.70683

2 MCMB 250 330 0.84 310000 10 95.03029 84.28352 43.89811 169.37659 6.6438 5.92961 2.99662 13.52682

3 MCMB 250 330 0.84 350000 10 120.76287 111.57879 46.19356 215.05619 6.53044 5.77192 3.05477 12.86145

4 MCMB 250 330 0.84 310000 20 124.34067 -3.21347 124.29914 -211.78021 7.90313 -3.23609 7.21022 -16.62939

Average absolute error: 116.71865 75.883393 71.541703 205.42467 6.8024425 5.07231 4.064005 14.431123

Table A-52: B743 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 330 0.84 210000 10 210.11645 -177.36523 112.6521 -367.81228 5.63259 -1.34041 5.47077 11.30617

2 MCMB 250 330 0.84 310000 10 68.15521 16.4824 66.13217 177.81982 4.47509 0.49308 4.44784 10.12617

3 MCMB 250 330 0.84 350000 10 78.61412 51.17002 59.68089 200.96783 4.4509 0.71744 4.3927 9.46079

4 MCMB 250 330 0.84 310000 20 207.38973 -128.26292 162.96971 -367.06119 17.28561 -17.14292 2.21648 -19.6555

Average absolute error: 141.06888 93.320143 100.35872 278.41528 7.9610475 4.9234625 4.1319475 12.637158

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 60

A.27 B744

Table A-53: B744 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 340 340 0.84 178800 10 116.02015 -48.3207 105.47884 -413.21529 6.33436 4.90697 4.00572 13.329

2 MCMB 340 340 0.84 285700 10 104.41655 62.13644 83.9159 -190.40998 6.17095 4.68987 4.0107 13.09284

3 MCMB 340 340 0.84 396800 10 80.0566 43.34677 67.30614 -193.1447 6.7249 5.61701 3.69777 12.30889

4 MCMB 340 340 0.84 285700 20 55.72645 -2.62082 55.66479 -155.49751 4.06402 1.37423 3.82462 10.32187

Average absolute error: 89.054938 39.106183 78.091418 238.06687 5.8235575 4.14702 3.8847025 12.26315

Table A-54: B744 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 340 340 0.84 178800 10 243.45819 -159.14135 184.24419 -664.19631 7.10468 -2.09687 6.7882 -13.54076

2 MCMB 340 340 0.84 285700 10 77.78254 -21.47506 74.75925 -232.04017 7.20841 -1.78721 6.98334 -13.71924

3 MCMB 340 340 0.84 396800 10 60.99788 -11.83263 59.8392 -189.56487 5.03726 0.74979 4.98114 9.59401

4 MCMB 340 340 0.84 285700 20 169.0745 -129.87942 108.24751 -414.99148 19.83008 -15.41441 12.47511 -35.49553

Average absolute error: 137.82828 80.582115 106.77254 375.19821 9.7951075 5.01207 7.8069475 18.087385

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 61

A.28 B752

Table A-55: B752 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 290 290 0.78 95200 10 63.84943 36.15786 52.6247 -161.05228 2.41453 1.76273 1.65006 4.68292

2 MCMB 290 290 0.78 62100 10 74.01703 -51.14683 53.50255 -166.90371 2.39894 1.7779 1.61058 4.71338

3 MCMB 290 290 0.78 115900 10 59.62494 54.5089 24.16428 92.81445 2.41097 1.64642 1.76126 6.36229

4 MCMB 290 290 0.78 95200 20 77.73202 3.84071 77.63708 209.65254 3.33371 2.46421 2.24527 6.31634

Average absolute error: 68.805855 36.413575 51.982153 157.60575 2.6395375 1.912815 1.8167925 5.5187325

Table A-56: B752 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 290 290 0.78 95200 10 72.50525 -37.35576 62.14144 -171.45852 1.73479 -0.18323 1.72509 3.73089

2 MCMB 290 290 0.78 62100 10 183.61704 -158.04592 93.47034 -373.26619 1.68828 -0.24467 1.67046 3.97587

3 MCMB 290 290 0.78 115900 10 28.62562 -5.99379 27.99108 -78.12023 1.86681 -0.09992 1.86413 3.7858

4 MCMB 290 290 0.78 95200 20 176.05331 -124.36471 124.61215 -287.48097 4.96601 -3.37399 3.64382 -6.89792

Average absolute error: 115.20031 81.440045 77.053753 227.58148 2.5639725 0.9754525 2.225875 4.59762

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 62

A.29 B753

Table A-57: B753 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 290 290 0.78 64600 10 66.60537 -12.00801 65.51399 150.23358 2.7589 2.02938 1.86899 5.0544

2 MCMB 290 290 0.78 101600 10 42.67858 10.35638 41.40298 -183.67747 2.72032 1.91004 1.93699 5.64056

3 MCMB 290 290 0.78 122500 10 41.18146 8.35366 40.32529 -135.6192 2.41967 1.58991 1.824 6.31693

4 MCMB 290 290 0.78 101600 20 50.90335 1.86792 50.86907 125.76801 3.8359 2.92679 2.47953 8.26231

Average absolute error: 50.34219 8.1464925 49.527833 148.82457 2.9336975 2.11403 2.0273775 6.31855

Table A-58: B753 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 290 290 0.78 64600 10 160.09745 -105.64005 120.29703 -284.44213 1.91343 -0.11623 1.9099 4.47501

2 MCMB 290 290 0.78 101600 10 68.10267 -51.58665 44.46111 -170.34067 1.99536 -0.05394 1.99463 4.23787

3 MCMB 290 290 0.78 122500 10 47.12815 -41.88968 21.59438 -130.27037 2.1074 -0.14566 2.10236 4.17484

4 MCMB 290 290 0.78 101600 20 149.50178 -107.60948 103.78334 -224.65919 4.81117 -2.75557 3.94388 -6.78607

Average absolute error: 106.20751 76.681465 72.533965 202.42809 2.70684 0.76785 2.4876925 4.9184475

Page 79: EUROCONTROL · 2019-02-18 · The information contained in this document may not be modified without prior written permission from EUROCONTROL. EUROCONTROL makes no warranty, either

Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 63

A.30 B762

Table A-59: B762 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 290 0.78 110000 10 62.89625 -13.36124 61.46068 125.04104 3.29096 2.42548 2.2243 7.10621

2 MCMB 250 290 0.78 140000 10 57.26028 3.59815 57.14712 -148.29217 3.24994 2.30273 2.29337 6.79694

3 MCMB 250 290 0.78 160000 10 43.48638 13.82212 41.23123 109.64972 3.21346 2.16214 2.37728 8.03729

4 MCMB 250 290 0.78 140000 20 65.52341 0.9166 65.517 150.00648 3.59323 2.56197 2.51945 7.44024

Average absolute error: 57.29158 7.9245275 56.339008 133.24735 3.3368975 2.36308 2.3536 7.34517

Table A-60: B762 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 290 0.78 110000 10 121.37326 -82.39532 89.1206 -265.08151 2.37664 -0.67405 2.27905 5.56191

2 MCMB 250 290 0.78 140000 10 87.9472 -55.75218 68.01768 -168.92657 2.39929 -0.56503 2.33181 5.25264

3 MCMB 250 290 0.78 160000 10 61.51928 -39.87033 46.8506 -126.02054 2.51509 -0.48894 2.46711 5.23714

4 MCMB 250 290 0.78 140000 20 158.8466 -105.31379 118.91697 -293.06918 6.52537 -4.49895 4.72651 -9.97768

Average absolute error: 107.42159 70.832905 80.726463 213.27445 3.4540975 1.5567425 2.95112 6.5073425

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 64

A.31 B763

Table A-61: B763 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 290 290 0.78 90000 10 80.63107 -30.77974 74.525 174.33854 3.05114 2.36612 1.92638 6.92814

2 MCMB 290 290 0.78 150000 10 74.78464 26.94058 69.76351 -198.24807 3.02344 2.33849 1.91641 6.84746

3 MCMB 290 290 0.78 180000 10 72.10481 31.90128 64.66383 -267.06 3.07997 2.40117 1.92888 6.82617

4 MCMB 290 290 0.78 150000 20 68.81396 -1.48626 68.79791 -206.01399 3.3603 2.85996 1.76416 6.77438

Average absolute error: 74.08362 22.776965 69.437563 211.41515 3.1287125 2.491435 1.8839575 6.8440375

Table A-62: B763 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 290 290 0.78 90000 10 196.76805 -143.64707 134.47373 -400.29759 2.91572 -1.31344 2.60313 -5.13036

2 MCMB 290 290 0.78 150000 10 88.36677 -46.962 74.85491 -188.01674 2.80841 -1.09059 2.588 -5.55794

3 MCMB 290 290 0.78 180000 10 67.84852 -29.32844 61.18222 -263.55812 2.56359 -0.78346 2.44094 -4.63352

4 MCMB 290 290 0.78 150000 20 169.8555 -143.15875 91.41369 -263.724 6.20113 -3.99617 4.74179 -12.70938

Average absolute error: 130.70971 90.774065 90.481138 278.89911 3.6222125 1.795915 3.093465 7.0078

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 65

A.32 B764

Table A-63: B764 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 290 290 0.78 103200 10 95.30295 -57.69751 75.85282 -316.53713 3.11223 2.59551 1.71735 7.57569

2 MCMB 290 290 0.78 158800 10 68.86665 44.48219 52.57328 -136.26597 2.94815 2.38815 1.72867 5.58831

3 MCMB 290 290 0.78 204100 10 94.9847 81.54674 48.70547 131.93426 3.12203 2.63847 1.669 5.39544

4 MCMB 290 290 0.78 158800 20 65.17832 5.009 64.98557 -158.9819 1.63079 0.9886 1.29698 3.38319

Average absolute error: 81.083155 47.18386 60.529285 185.92982 2.7033 2.1526825 1.603 5.4856575

Table A-64: B764 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 290 290 0.78 103200 10 203.02989 -162.09609 122.25381 -528.10595 3.28245 -1.60269 2.86459 -6.12946

2 MCMB 290 290 0.78 158800 10 63.85704 -32.28123 55.09668 -201.90445 3.34411 -1.54738 2.96457 -6.92404

3 MCMB 290 290 0.78 204100 10 51.52025 22.79757 46.20181 -129.05133 2.71603 -0.87878 2.56993 -5.58412

4 MCMB 290 290 0.78 158800 20 174.28765 -130.67387 115.32791 -382.47819 8.81058 -7.58154 4.4885 -17.3292

Average absolute error: 123.17371 86.96219 84.720053 310.38498 4.5382925 2.9025975 3.2218975 8.991705

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 66

A.33 B772

Table A-65: B772 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 310 310 0.84 138100 10 127.30465 -24.10063 125.00254 307.88678 7.84331 3.80893 6.85636 15.61499

2 MCMB 310 310 0.84 208700 10 104.39945 13.32234 103.54593 -309.02702 7.89321 3.75119 6.94488 15.57923

3 MCMB 310 310 0.84 286900 10 57.67762 15.61634 55.52331 -159.32931 7.743 2.85557 7.1972 18.56508

4 MCMB 310 310 0.84 208700 20 125.57778 2.0737 125.56066 309.01994 7.91654 2.38235 7.54957 14.51223

Average absolute error: 103.73988 13.778253 102.40811 271.31576 7.849015 3.19951 7.1370025 16.067883

Table A-66: B772 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 310 310 0.84 138100 10 194.03956 -120.18136 152.34104 334.10565 6.45776 -0.84227 6.4026 11.64067

2 MCMB 310 310 0.84 208700 10 121.45571 -51.43745 110.02581 -276.33 6.56679 -0.86018 6.51021 12.35969

3 MCMB 310 310 0.84 286900 10 59.77608 -34.17448 49.0437 -141.88955 7.17482 -1.39609 7.03768 13.46079

4 MCMB 310 310 0.84 208700 20 205.24335 -106.24593 175.60363 386.3562 12.22724 -8.77944 8.51039 -17.12974

Average absolute error: 145.12868 78.009805 121.75355 284.67035 8.1066525 2.969495 7.11522 13.647723

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 67

A.34 B773

Table A-67: B773 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 310 310 0.84 159600 10 82.8059 -63.28874 53.39805 -198.00078 5.42073 3.66965 3.98973 9.95081

2 MCMB 310 310 0.84 237600 10 68.47963 52.36476 44.12926 152.78439 5.35625 3.3401 4.18726 9.65233

3 MCMB 310 310 0.84 299300 10 83.86524 80.31929 24.12862 118.61955 4.90594 2.65004 4.12863 12.09931

4 MCMB 310 310 0.84 237600 20 36.91752 -3.49329 36.75188 -79.35915 5.48891 -1.22073 5.35144 -8.99334

Average absolute error: 68.017073 49.86652 39.601953 137.19097 5.2929575 2.72013 4.414265 10.173948

Table A-68: B773 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 310 310 0.84 159600 10 181.89238 -142.07471 113.57646 -303.73665 3.93255 -0.91539 3.82453 -9.44073

2 MCMB 310 310 0.84 237600 10 59.78716 -13.33795 58.28039 137.52875 4.2497 -0.78476 4.17661 -9.75653

3 MCMB 310 310 0.84 299300 10 41.97 29.11607 30.22806 104.68879 4.47945 -0.94513 4.37861 -9.71668

4 MCMB 310 310 0.84 237600 20 122.52787 -110.6778 52.56904 -182.25075 13.18929 -9.03353 9.61002 -22.36722

Average absolute error: 101.54435 73.801633 63.663488 182.05124 6.4627475 2.9197025 5.4974425 12.82029

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 68

A.35 BE9L

Table A-69: BE9L with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 150 150 0.32 3600 10 272.82212 -52.32956 267.7565 516.6492 1.13275 0.43798 1.04465 2.69953

2 MCMB 150 150 0.32 4200 10 81.50385 28.50566 76.35644 188.952 0.62726 0.13699 0.61212 1.00038

3 MCMB 150 150 0.32 4600 10 144.18728 26.64695 141.7036 295.6592 0.61824 0.11958 0.60656 1.23286

4 MCMB 150 150 0.32 4300 20 87.74317 4.34967 87.6353 -146.013 0.35243 -0.19631 0.29269 -0.47754

Average absolute error: 146.56411 27.95796 143.36296 286.81835 0.68267 0.222715 0.639005 1.3525775

Table A-70: BE9L with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 150 150 0.32 3600 10 271.20999 -85.2461 257.46449 458.02476 1.1043 0.3335 1.05274 2.60093

2 MCMB 150 150 0.32 4200 10 70.15433 0.25754 70.15386 144.83093 0.65263 0.03401 0.65175 -0.97077

3 MCMB 150 150 0.32 4600 10 135.33296 1.56259 135.32394 259.92652 0.62086 0.02641 0.62029 1.13427

4 MCMB 150 150 0.32 4300 20 97.2235 -27.62834 93.21526 -189.7446 0.46442 -0.34226 0.31393 -0.69942

Average absolute error: 143.4802 28.673643 139.03939 263.1317 0.7105525 0.184045 0.6596775 1.3513475

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 69

A.36 BE20

Table A-71: BE20 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 155 135 0.3 4600 10 162.47357 -22.03471 160.97245 343.74617 2.44903 0.35155 2.42367 5.06317

2 MCMB 155 135 0.3 5100 10 171.73482 -3.38668 171.70142 430.85498 2.26307 0.23312 2.25103 6.07705

3 MCMB 155 135 0.3 5670 10 123.77016 4.27305 123.69638 251.47328 1.27438 -0.0836 1.27163 -3.00794

4 MCMB 155 135 0.3 5100 20 89.97124 26.00815 86.13013 166.6786 1.4986 0.17905 1.48787 2.60041

Average absolute error: 136.98745 13.925648 135.6251 298.18826 1.87127 0.21183 1.85855 4.1871425

Table A-72: BE20 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 155 135 0.3 4600 10 189.1465 -101.04158 159.89683 -379.60193 2.40944 0.26298 2.39505 4.89347

2 MCMB 155 135 0.3 5100 10 189.29735 -74.02282 174.22431 -410.74403 2.21934 0.14455 2.21463 5.90735

3 MCMB 155 135 0.3 5670 10 131.47385 -57.57634 118.19619 -234.41315 1.25922 -0.17217 1.24739 -3.06466

4 MCMB 155 135 0.3 5100 20 128.69441 -106.09363 72.84499 -208.46659 1.44648 0.0108 1.44644 -2.63956

Average absolute error: 159.65303 84.683593 131.29058 308.30643 1.83362 0.147625 1.8258775 4.12626

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 70

A.37 BE58

Table A-73: BE58 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 139 139 0.28 1800 10 106.35682 10.91142 105.79563 -210.70709 0.28807 0.10141 0.26963 0.42337

2 MCMB 139 139 0.28 2200 10 85.12037 18.00169 83.19505 -119.28261 0.1017 0.03321 0.09612 0.20719

3 MCMB 139 139 0.28 2450 10 57.74245 -8.653 57.09043 98.96522 0.21813 -0.11064 0.18799 -0.3589

Average absolute error: 83.073213 12.522037 82.027037 142.98497 0.2026333 0.0817533 0.18458 0.32982

Table A-74: BE58 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 139 139 0.28 1800 10 115.52329 -32.00435 111.00158 -264.74537 0.28807 0.10141 0.26963 0.42337

2 MCMB 139 139 0.28 2200 10 89.69221 -10.28273 89.10083 -158.17311 0.1017 0.03321 0.09612 0.20719

3 MCMB 139 139 0.28 2450 10 68.99194 -28.53242 62.81552 -106.0252 0.21813 -0.11064 0.18799 -0.3589

Average absolute error: 91.40248 23.6065 87.63931 176.31456 0.2026333 0.0817533 0.18458 0.32982

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 71

A.38 C130

Table A-75: C130 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 170 170 0.5 36400 10 42.00463 1.09644 41.99032 107.90155 4.16726 -0.21704 4.16161 12.51812

2 MCMB 170 170 0.5 59100 10 31.88146 6.30505 31.25179 98.07585 1.08048 -0.28922 1.04105 -2.54507

3 MCMB 170 170 0.5 72700 10 24.33553 -14.39573 19.62093 -51.95882 9.61292 0.21384 9.61054 25.74877

4 MCMB 170 170 0.5 59100 20 21.99383 0.91409 21.97483 -46.39113 2.16127 -0.56871 2.08511 -6.01556

Average absolute error: 30.053863 5.6778275 28.709468 76.081838 4.2554825 0.3222025 4.2245775 11.70688

Table A-76: C130 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 170 170 0.5 36400 10 87.17218 -70.43257 51.36383 -138.38446 4.35321 -1.00486 4.23565 -12.46523

2 MCMB 170 170 0.5 59100 10 45.26058 -32.07418 31.93378 -81.18752 1.603 -1.00687 1.24732 -3.40594

3 MCMB 170 170 0.5 72700 10 51.75934 -43.46392 28.10545 -98.02443 9.69087 -0.38535 9.6832 25.49087

4 MCMB 170 170 0.5 59100 20 80.29041 -67.2124 43.92087 -161.16627 2.97683 -1.84282 2.33785 -7.91169

Average absolute error: 66.120628 53.295768 38.830983 119.69067 4.6559775 1.059975 4.376005 12.318433

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 72

A.39 C510

Table A-77: C510 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 170 170 0.44 3930 10 111.47253 79.48015 78.16029 222.07105 0.75722 -0.17595 0.73649 1.36112

2 MCMB 170 170 0.44 3410 10 80.83242 10.6406 80.12901 158.4237 0.99542 -0.29908 0.94943 -2.40495

3 MCMB 170 170 0.44 2950 10 114.83475 -68.567 92.11724 -228.22699 1.87016 0.29806 1.84626 4.76962

4 MCMB 170 170 0.44 3930 20 133.35968 67.07157 115.26582 343.70576 0.83729 0.39414 0.73872 2.46768

5 MCMB 170 170 0.44 3410 20 136.76081 -0.13099 136.76074 339.20459 0.68262 0.27737 0.62373 1.46707

6 MCMB 170 170 0.44 2950 20 179.20621 -74.59318 162.94393 335.35205 0.92022 0.30201 0.86925 1.6944

Average absolute error: 141.04036 52.590685 126.77193 311.62235 1.0775725 0.317895 1.01949 2.5996925

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 73

Table A-78: C510 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 170 170 0.44 3930 10 74.9199 20.33931 72.10619 147.4199 0.87332 -0.38353 0.78459 -1.49605

2 MCMB 170 170 0.44 3410 10 89.90144 -50.16703 74.60254 -207.90641 1.07663 -0.44241 0.98153 -2.40495

3 MCMB 170 170 0.44 2950 10 152.40176 -129.62322 80.1506 -291.58736 2.12232 0.1957 2.11328 4.50554

4 MCMB 170 170 0.44 3930 20 94.85554 -6.49607 94.63284 211.45814 0.96318 -0.03297 0.96261 2.46768

5 MCMB 170 170 0.44 3410 20 139.15979 -81.50494 112.79359 -234.39767 0.7017 -0.01858 0.70146 1.27974

6 MCMB 170 170 0.44 2950 20 212.62978 -165.29041 133.75539 -345.28521 0.83935 -0.04084 0.83836 1.21188

Average absolute error: 149.76172 95.72866 105.33311 270.6821 1.1566375 0.0720225 1.1539275 2.36621

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 74

A.40 C550

Table A-79: C550 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 220 210 0.63 6025 10 111.30298 -0.08567 111.30295 -198.22235 0.98654 0.27105 0.94858 2.23606

Average absolute error: 111.30298 0.08567 111.30295 198.22235 0.98654 0.27105 0.94858 2.23606

Table A-80: C550 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 220 210 0.63 6025 10 121.45258 -38.12929 115.31212 -265.34122 1.03711 0.11694 1.0305 2.23606

Average absolute error: 121.45258 38.12929 115.31212 265.34122 1.03711 0.11694 1.0305 2.23606

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 75

A.41 C560

Table A-81: C560 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 250 0.55 5450 10 366.51796 5.23544 366.48057 -904.20253 1.84276 0.12534 1.83849 -4.1984

2 MCMB 250 250 0.55 6360 10 319.39327 47.1257 315.8975 750.54631 2.1739 0.34837 2.14581 5.97438

3 MCMB 250 250 0.55 7200 10 191.51785 7.04655 191.38817 382.51677 1.62984 0.03949 1.62936 4.18261

Average absolute error: 292.47636 19.802563 291.25541 679.08854 1.8821667 0.1710667 1.87122 4.78513

Table A-82: C560 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 250 0.55 5450 10 355.28437 -41.59608 352.84097 -905.04798 2.01867 -0.46079 1.96537 -4.75481

2 MCMB 250 250 0.55 6360 10 302.44259 4.636 302.40705 687.39478 2.28572 -0.23776 2.27332 5.72003

3 MCMB 250 250 0.55 7200 10 187.62542 -29.82441 185.23985 -408.67927 1.79211 -0.50066 1.72075 4.01508

Average absolute error: 281.78413 25.352163 280.16262 667.04068 2.0321667 0.3997367 1.98648 4.8299733

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 76

A.42 C750

Table A-83: C750 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 300 300 0.8 11500 10 329.91685 -143.62045 297.01565 -730.65648 5.5311 -0.93288 5.45186 11.39635

2 MCMB 300 300 0.8 14500 10 195.07676 21.36547 193.90322 463.32336 1.93076 0.55786 1.84841 4.63085

3 MCMB 300 300 0.8 16190 10 274.45673 94.38406 257.71719 858.53498 2.85194 1.21842 2.57857 5.9934

4 MCMB 300 300 0.8 14500 20 198.95526 43.71552 194.09314 535.32505 3.63139 2.20476 2.88549 7.60333

Average absolute error: 249.6014 75.771375 235.6823 646.95997 3.4862975 1.22848 3.1910825 7.4059825

Table A-84: C750 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 300 300 0.8 11500 10 324.61532 -166.05238 278.92959 -772.98456 6.35462 -1.94332 6.05018 -11.99406

2 MCMB 300 300 0.8 14500 10 169.09526 4.3906 169.03825 377.2965 2.11285 -0.11131 2.10992 3.95172

3 MCMB 300 300 0.8 16190 10 255.02475 74.80527 243.80688 770.67321 2.82779 0.37562 2.80273 5.9934

4 MCMB 300 300 0.8 14500 20 188.67277 20.59776 187.54505 419.55096 3.1592 0.57656 3.10615 7.01339

Average absolute error: 234.35203 66.461503 219.82994 585.12631 3.613615 0.7517025 3.517245 7.2381425

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 77

A.43 CL60

Table A-85: CL60 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 250 0.72 20910 5 192.85569 123.68932 147.96712 386.77477 0.8818 0.11107 0.87478 2.00693

2 MCMB 250 250 0.72 12700 10 243.02355 156.99132 185.51058 453.58218 0.51991 -0.08394 0.51309 1.04967

3 MCMB 250 250 0.72 20000 10 182.92437 124.0554 134.43059 267.36201 0.87358 0.04213 0.87256 -1.25387

4 MCMB 250 250 0.72 22700 10 147.04098 101.64939 106.24712 271.96194 0.60315 0.07343 0.59867 1.23106

5 MCMB 300 300 0.72 16400 10 285.86615 -172.04552 228.2976 -487.20804 1.07732 -0.05866 1.07572 -2.84261

6 MCMB 300 300 0.72 20000 10 238.0416 -121.87498 204.47565 414.77688 0.86497 -0.112 0.85769 -2.21647

Average absolute error: 214.95872 133.38432 167.82144 380.27764 0.803455 0.080205 0.7987517 1.7667683

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 78

Table A-86: CL60 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 250 0.72 20910 5 179.56254 117.18207 136.05539 356.34389 0.96699 -0.32515 0.91069 1.71789

2 MCMB 250 250 0.72 12700 10 267.91411 149.99014 221.99308 -407.19448 1.07697 -0.97895 0.44891 -1.68698

3 MCMB 250 250 0.72 20000 10 172.73474 114.1991 129.59883 240.44448 1.23257 -0.78538 0.94996 -2.3637

4 MCMB 250 250 0.72 22700 10 130.9941 89.83922 95.33294 225.85749 0.9806 -0.6907 0.69607 -1.77102

5 MCMB 300 300 0.72 16400 10 219.96401 -110.40968 190.24687 -380.02493 1.39575 -1.10838 0.8483 -3.32614

6 MCMB 300 300 0.72 20000 10 183.90822 -74.47115 168.15552 372.73851 1.29577 -1.11141 0.66618 -2.7

Average absolute error: 192.51295 109.34856 156.89711 330.43396 1.1581083 0.8333283 0.7533517 2.260955

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 79

A.44 CRJ1

Table A-87: CRJ1 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 290 0.74 17000 10 128.33122 64.21951 111.10696 206.04976 1.272 0.34642 1.22392 2.21777

2 MCMB 250 290 0.74 21000 10 76.98986 -20.62293 74.17636 -173.96732 1.21395 0.35624 1.16051 2.78237

3 MCMB 250 290 0.74 24000 10 105.95916 -77.04524 72.74184 -190.15 0.99089 0.01372 0.9908 2.02277

4 MCMB 250 290 0.74 21000 20 86.23867 -1.15193 86.23098 155.24567 1.15496 0.45826 1.06015 2.57477

Average absolute error: 99.379728 40.759903 86.064035 181.35319 1.15795 0.29366 1.108845 2.39942

Table A-88: CRJ1 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 290 0.74 17000 10 191.77019 66.55947 179.84894 320.26214 1.16116 -0.71277 0.91665 -2.51781

2 MCMB 250 290 0.74 21000 10 114.43917 -20.73625 112.54479 -282.01529 1.18268 -0.62318 1.00518 -2.39281

3 MCMB 250 290 0.74 24000 10 121.70236 -89.07495 82.9284 -281.7212 1.26822 -0.87911 0.91408 -2.41781

4 MCMB 250 290 0.74 21000 20 154.77972 -48.1668 147.09425 -296.12172 1.40488 -1.06007 0.92192 -2.73935

Average absolute error: 145.67286 56.134368 130.6041 295.03009 1.254235 0.8187825 0.9394575 2.516945

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 80

A.45 CRJ2

Table A-89: CRJ2 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 290 0.74 19090 10 129.63944 35.10468 124.79601 247.59442 1.26894 0.67569 1.07408 2.77641

2 MCMB 250 290 0.74 21818 10 87.41177 -11.16819 86.69538 -160.17257 1.03864 0.52426 0.89663 2.58476

3 MCMB 250 290 0.74 24545 10 69.03153 -22.30926 65.32724 -130.80537 1.24241 0.3007 1.20547 2.639

4 MCMB 250 290 0.74 20910 20 94.33595 9.26382 93.87999 -147.20681 1.51213 1.07149 1.06699 3.00416

Average absolute error: 95.104673 19.461488 92.674655 171.44479 1.26553 0.643035 1.0607925 2.7510825

Table A-90: CRJ2 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 290 0.74 19090 10 157.90312 33.24874 154.36294 -249.95343 1.27421 -0.27503 1.24417 2.55276

2 MCMB 250 290 0.74 21818 10 117.61152 -16.94212 116.38485 -207.9484 0.98425 -0.35739 0.91708 2.1374

3 MCMB 250 290 0.74 24545 10 114.6624 -30.37081 110.56708 -195.82558 1.20706 -0.54813 1.07543 2.19164

4 MCMB 250 290 0.74 20910 20 235.74889 29.1365 233.94145 324.58081 1.09695 -0.5699 0.93729 2.16883

Average absolute error: 156.48148 27.424543 153.81408 244.57706 1.1406175 0.4376125 1.0434925 2.2626575

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 81

A.46 CRJ9

Table A-91: CRJ9 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 290 0.74 36360 10 108.536 -17.78674 107.06865 -184.76003 1.67371 0.01632 1.67363 -3.36732

2 MCMB 250 290 0.74 39090 10 107.38166 28.96495 103.40141 -174.79169 1.46108 0.72509 1.26847 3.90468

3 MCMB 250 290 0.74 33640 10 145.60722 -7.38586 145.41977 299.22368 1.83442 0.65316 1.7142 5.72318

4 MCMB 250 290 0.74 33640 20 129.74063 8.88472 129.43605 -260.27702 1.57737 1.07168 1.15741 2.53214

Average absolute error: 122.81638 15.755568 121.33147 229.76311 1.636645 0.6165625 1.4534275 3.88183

Table A-92: CRJ9 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 290 0.74 36360 10 143.61478 -57.36327 131.66116 -246.8808 1.67599 -0.90384 1.41139 -3.36732

2 MCMB 250 290 0.74 39090 10 115.60531 -11.47266 115.03463 -241.13591 1.46764 -0.15589 1.45934 3.90468

3 MCMB 250 290 0.74 33640 10 152.5173 -49.62834 144.21704 -290.16379 1.96181 -0.3942 1.92179 5.72318

4 MCMB 250 290 0.74 33640 20 205.34999 -52.97119 198.40028 -392.03544 2.176 -1.56999 1.50668 -3.27704

Average absolute error: 154.27185 42.858865 147.32828 292.55399 1.82036 0.75598 1.5748 4.068055

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 82

A.47 D228

Table A-93: D228 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 165 165 0.32 5600 10 145.90811 -46.33206 138.35649 -237.0976 0.87283 -0.21097 0.84694 -1.84319

2 MCMB 165 165 0.32 5000 10 364.92138 8.32685 364.82637 787.96844 1.55349 0.18646 1.54226 3.45129

3 MCMB 165 165 0.32 6400 10 142.6755 5.87249 142.55459 281.3151 1.28353 0.05826 1.28221 3.34324

4 MCMB 165 165 0.32 5600 20 150.14774 18.842 148.96081 280.47089 1.03164 0.50533 0.8994 2.29591

Average absolute error: 200.91318 19.84335 198.67457 396.71301 1.1853725 0.240255 1.1427025 2.7334075

Table A-94: D228 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 165 165 0.32 5600 10 158.73408 -84.37921 134.44946 -271.10441 0.8778 -0.253 0.84055 -1.92452

2 MCMB 165 165 0.32 5000 10 354.83643 -37.9502 352.80119 713.60741 1.54042 0.14444 1.53363 3.42922

3 MCMB 165 165 0.32 6400 10 139.80107 -27.12895 137.14357 239.50496 1.28433 0.01623 1.28423 3.28722

4 MCMB 165 165 0.32 5600 20 144.82756 -40.86551 138.94255 -280.00458 0.99318 0.42778 0.89634 2.22951

Average absolute error: 199.54979 47.580968 190.83419 376.05534 1.1739325 0.2103625 1.1386875 2.7176175

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 83

A.48 D328

Table A-95: D328 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 180 180 NaN 12000 10 179.6631 -9.60721 179.40605 -316.59009 1.15018 0.26454 1.11934 3.07958

2 MCMB 180 180 NaN 11000 10 233.01396 -39.82263 229.58585 -499.17044 1.45873 0.13974 1.45202 -3.21101

3 MCMB 180 180 NaN 13640 10 148.29043 28.23419 145.57775 252.44736 1.07967 0.23207 1.05443 1.99276

4 MCMB 180 180 NaN 12000 20 232.01987 -14.8251 231.54576 370.46394 1.1002 0.46169 0.99864 2.37601

Average absolute error: 198.24684 23.122283 196.52885 359.66796 1.197195 0.27451 1.1561075 2.66484

Table A-96: D328 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 180 180 NaN 12000 10 191.37175 -87.18592 170.35774 -375.31116 1.15181 0.11749 1.1458 2.90826

2 MCMB 180 180 NaN 11000 10 253.01849 -126.28359 219.25057 -558.15655 1.46875 -0.00731 1.46873 -3.48946

3 MCMB 180 180 NaN 13640 10 142.67732 -37.13256 137.76063 -284.36802 1.08031 0.08502 1.07696 1.84092

4 MCMB 180 180 NaN 12000 20 258.84987 -151.40049 209.9551 -464.35297 1.09092 0.18545 1.07504 2.05357

Average absolute error: 211.47936 100.50064 184.33101 420.54718 1.1979475 0.0988175 1.1916325 2.5730525

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 84

A.49 DA42

Table A-97: DA42 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 85 85 NaN 1400 10 73.35595 -42.9393 59.47529 -156.949 0.12125 0.00009 0.12125 -0.22426

2 MCMB 85 85 NaN 1600 10 55.58959 20.3974 51.71217 -92.6254 0.12134 0 0.12134 -0.22448

3 MCMB 85 85 NaN 1785 10 46.23986 25.18805 38.7774 70.63218 0.1214 -0.00009 0.1214 -0.22458

4 MCMB 85 85 NaN 1600 20 59.45097 9.35542 58.71025 -117.647 0.12126 0.00005 0.12126 -0.22436

Average absolute error: 58.659093 24.470043 52.168778 109.4634 0.1213125 0.0000575 0.1213125 0.22442

Table A-98: DA42 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 85 85 NaN 1400 10 106.5818 -89.201 58.33411 -204.693 0.12125 0.00009 0.12125 -0.22426

2 MCMB 85 85 NaN 1600 10 54.51327 -19.0432 51.07889 -132.83 0.12134 0 0.12134 -0.22448

3 MCMB 85 85 NaN 1785 10 38.22402 -7.49108 37.48279 -81.1985 0.1214 -0.00009 0.1214 -0.22458

4 MCMB 85 85 NaN 1600 20 86.97725 -64.0139 58.88348 -191.945 0.12126 0.00005 0.12126 -0.22436

Average absolute error: 71.574085 44.937295 51.444818 152.66663 0.1213125 0.0000575 0.1213125 0.22442

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 85

A.50 DH8A

Table A-99: DH8A with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 160 160 0.4 12000 10 309.779 7.76993 309.68154 650.67239 1.90804 0.17968 1.89957 3.82456

2 MCMB 160 160 0.4 14500 10 165.1249 -40.0885 160.1848 538.7422 1.84989 -0.3958 1.80705 -5.015

3 MCMB 160 160 0.4 15600 10 190.70636 2.48091 190.69022 647.46772 1.9971 0.24479 1.98204 6.06222

4 MCMB 125 125 0.32 15650 20 146.0771 7.35336 145.8919 300.39651 1.10654 -0.71152 0.84745 -2.1121

Average absolute error: 202.92184 14.423175 201.61212 534.31971 1.7153925 0.3829475 1.6340275 4.25347

Table A-100: DH8A with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 160 160 0.4 12000 10 300.95184 -56.81842 295.53964 558.62623 1.95177 0.08224 1.95004 3.78945

2 MCMB 160 160 0.4 14500 10 178.95947 -86.6638 156.57547 476.01483 1.86752 -0.49324 1.80121 -5.20643

3 MCMB 160 160 0.4 15600 10 187.76374 -39.41596 183.57997 582.52612 2.00656 0.14735 2.00115 5.94743

4 MCMB 125 125 0.32 15650 20 148.47228 -71.778 129.96899 -271.93553 1.30311 -0.88499 0.9565 -2.43432

Average absolute error: 204.03683 63.669045 191.41602 472.27568 1.78224 0.401955 1.677225 4.3444075

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 86

A.51 DH8C

Table A-101: DH8C with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 165 165 0.33 17000 10 114.13253 3.14154 114.08929 175.88513 1.113 -0.07399 1.11054 -1.97285

2 MCMB 165 165 0.33 19500 10 111.50693 -7.34242 111.26493 -208.06771 1.34078 -0.03343 1.34036 4.18424

3 MCMB 165 165 0.33 17000 20 103.67998 -3.28718 103.62786 171.56458 0.82867 -0.10586 0.82188 1.78104

Average absolute error: 109.77315 4.59038 109.66069 185.17247 1.09415 0.0710933 1.0909267 2.6460433

Table A-102: DH8C with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 165 165 0.33 17000 10 113.30284 -44.65343 104.13263 -202.77187 1.13717 -0.23677 1.11225 -2.21293

2 MCMB 165 165 0.33 19500 10 115.48664 -45.6985 106.06041 -252.03918 1.31098 -0.19621 1.29621 3.8947

3 MCMB 165 165 0.33 17000 20 116.15355 -76.84737 87.09838 -213.71979 0.93203 -0.42304 0.83049 -1.52372

Average absolute error: 114.98101 55.7331 99.09714 222.84361 1.1267267 0.28534 1.07965 2.5437833

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 87

A.52 DH8D

Table A-103: DH8D with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 210 210 0.41 26000 10 294.75824 -2.6659 294.74618 -465.80057 4.45314 -0.2586 4.44562 -6.92161

2 MCMB 210 210 0.41 28000 10 326.78182 -31.15667 325.29312 600.76638 5.02322 -0.78832 4.96098 -11.3949

3 MCMB 210 210 0.41 29257 10 241.41665 37.73614 238.44912 633.5581 3.69701 0.16681 3.69325 9.62328

4 MCMB 210 210 0.41 26000 20 267.30333 -0.19572 267.30326 643.63124 3.71566 0.4956 3.68246 10.69716

Average absolute error: 282.56501 17.938608 281.44792 585.93907 4.2222575 0.4273325 4.1955775 9.6592375

Table A-104: DH8D with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 210 210 0.41 26000 10 236.17174 9.52827 235.97945 -392.51114 4.19971 0.49384 4.17058 -6.64467

2 MCMB 210 210 0.41 28000 10 307.84345 -42.72619 304.864 516.87407 4.43444 -0.2395 4.42797 7.92874

3 MCMB 210 210 0.41 29257 10 257.72409 -10.00762 257.52971 552.18225 4.14926 -0.09783 4.1481 9.3871

4 MCMB 210 210 0.41 26000 20 254.63833 -82.02056 241.06702 481.23723 3.84573 0.13067 3.84351 10.25215

Average absolute error: 264.0944 36.07066 259.86005 485.70117 4.157285 0.24046 4.14754 8.553165

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 88

A.53 E120

Table A-105: E120 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 150 150 0.37 11500 10 387.0789 38.43734 385.1657 882.0996 2.42804 0.08843 2.42643 5.71466

2 MCMB 150 150 0.37 10000 10 334.7891 6.13146 334.7329 -755.179 2.12622 0.10964 2.12339 -5.12865

3 MCMB 150 150 0.37 8500 10 378.9271 -41.1687 376.6841 748.1138 2.01718 -0.13566 2.01262 4.33616

4 MCMB 150 150 0.37 10000 20 371.1294 -13.024 370.9008 789.0999 2.08766 0.10532 2.085 5.07741

Average absolute error: 367.98113 24.690375 366.87088 793.62308 2.164775 0.1097625 2.16186 5.06422

Table A-106: E120 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 150 150 0.37 11500 10 368.3856 21.76763 367.742 821.0134 2.47119 -0.04073 2.47085 5.54001

2 MCMB 150 150 0.37 10000 10 317.4589 -11.8197 317.2388 -779.676 2.13021 -0.02021 2.13011 -5.2694

3 MCMB 150 150 0.37 8500 10 385.2752 -72.4896 378.3942 714.6272 2.07092 -0.31346 2.04706 -4.21455

4 MCMB 150 150 0.37 10000 20 341.0696 -57.7826 336.1394 666.2527 2.14251 -0.19206 2.13388 4.78206

Average absolute error: 353.04733 40.964883 349.8786 745.39233 2.2037075 0.141615 2.195475 4.951505

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 89

A.54 E135

Table A-107: E135 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 240 270 0.56 14000 15 99.39661 3.94279 99.31838 269.3008 0.49561 0.09469 0.48648 1.04367

2 MCMB 240 270 0.56 17000 15 73.69155 -8.21636 73.23207 188.1457 0.49502 0.10186 0.48443 0.92563

3 MCMB 240 270 0.56 20000 15 65.59881 -8.06129 65.1016 132.372 0.45275 0.20156 0.40541 0.87911

4 MCMB 240 270 0.56 14000 25 59.84651 13.64381 58.2705 210.7942 0.53174 0.44258 0.29475 1.12209

5 MCMB 240 270 0.56 17000 25 67.08263 -4.9196 66.90199 138.0168 0.54079 0.46096 0.28279 1.13081

6 MCMB 240 270 NaN 20000 25 55.1927 -11.817 53.91283 -119.914 0.76397 0.71414 0.27137 1.10212

Average absolute error: 70.134802 8.433475 69.456228 176.42392 0.5466467 0.335965 0.3708717 1.033905

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 90

Table A-108: E135 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 240 270 0.56 14000 15 69.88665 -33.6827 61.23412 -194.055 1.12342 -0.75342 0.83333 -2.05642

2 MCMB 240 270 0.56 17000 15 52.29842 -34.3975 39.39465 -124.882 1.12408 -0.74427 0.84239 -2.05651

3 MCMB 240 270 0.56 20000 15 49.49121 -27.5806 41.09366 -108.937 0.9773 -0.59934 0.77195 -1.69962

4 MCMB 240 270 0.56 14000 25 147.1211 11.10034 146.7017 -330.054 1.21642 -0.86614 0.8541 -1.83806

5 MCMB 240 270 0.56 17000 25 127.2376 0.72041 127.2356 -256.746 1.18401 -0.8316 0.84281 -1.68152

6 MCMB 240 270 NaN 20000 25 110.7215 -98.4668 50.63137 -207.331 0.58077 0.04364 0.57913 -0.87637

Average absolute error: 92.792747 34.324725 77.715183 203.6675 1.0343333 0.639735 0.787285 1.7014167

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 91

A.55 E145

Table A-109: E145 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 240 270 0.56 15000 15 77.52489 6.76022 77.22958 139.8099 0.71505 0.06523 0.71207 1.81157

2 MCMB 240 270 0.56 18500 15 60.23003 -7.18773 59.79961 -158.411 0.59949 0.08941 0.59278 1.55817

3 MCMB 240 270 0.56 22000 15 64.71452 -4.16918 64.58009 -153.163 0.5074 0.11296 0.49466 0.97254

4 MCMB 240 270 0.56 15000 25 79.03247 43.83206 65.76383 232.9885 0.71595 0.41642 0.5824 1.89196

5 MCMB 240 270 0.56 18000 25 78.68875 -59.5395 51.44869 -200.652 0.63912 0.44628 0.4575 1.55384

6 MCMB 240 270 0.56 22000 25 64.10138 10.68569 63.20445 -132.333 0.70609 0.47976 0.51806 2.15724

Average absolute error: 70.71534 22.029063 63.671042 169.55957 0.6471833 0.2683433 0.5595783 1.6575533

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 92

Table A-110: E145 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 240 270 0.56 15000 15 121.156 -68.4408 99.97314 -214.683 1.22509 -0.88707 0.84496 -2.06355

2 MCMB 240 270 0.56 18500 15 101.3572 -62.7189 79.62176 -198.691 1.12743 -0.84477 0.74664 -2.01693

3 MCMB 240 270 0.56 22000 15 90.86956 -46.4521 78.09919 -186.261 1.04772 -0.79915 0.67755 -1.86071

4 MCMB 240 270 0.56 15000 25 124.0562 -20.0801 122.4203 -210.522 1.50914 -1.04061 1.093 -2.63329

5 MCMB 240 270 0.56 18000 25 142.4704 -97.9731 103.4364 -230.212 1.44568 -1.00386 1.04032 -2.21449

6 MCMB 240 270 0.56 22000 25 96.30448 -18.4881 94.51319 -161.098 1.40972 -0.89701 1.0875 -2.29067

Average absolute error: 112.70231 52.35885 96.343997 200.2445 1.29413 0.9120783 0.914995 2.17994

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 93

A.56 E170

Table A-111: E170 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 240 290 NaN 23140 15 56.53682 -5.41258 56.27714 112.3639 0.9455 0.67268 0.66444 1.96562

2 MCMB 290 290 0.7 23140 15 99.91643 -16.4068 98.56018 256.4739 0.47709 0.3136 0.35953 1.22273

3 MCMB 240 290 NaN 30170 15 53.36405 25.77592 46.72605 118.6524 0.90552 0.49344 0.75927 1.95293

4 MCMB 290 290 0.7 30170 15 66.48068 1.04032 66.47254 -192.187 0.55223 0.25819 0.48816 -1.65175

5 MCMB 240 290 NaN 37200 15 51.63558 37.61074 35.37888 104.3352 0.83345 0.49485 0.67064 1.76523

6 MCMB 290 290 0.7 37200 15 53.88726 2.59691 53.82465 118.9222 0.59636 0.23738 0.54708 1.39066

7 MCMB 240 290 NaN 23140 25 118.7604 -103.244 58.69235 -154.068 0.9605 0.57629 0.7684 2.0386

8 MCMB 290 290 0.7 23140 25 155.5698 30.16063 152.6181 -360.698 0.92477 0.72821 0.57 1.39799

9 MCMB 240 290 NaN 30170 25 56.08886 -38.2694 41.00501 -86.1479 0.86594 0.58501 0.63846 1.56284

10 MCMB 290 290 0.7 30170 25 104.9603 39.89091 97.08435 -230.967 1.0015 0.69034 0.72555 -1.62747

11 MCMB 240 290 NaN 37200 25 37.73491 -19.6607 32.20842 -62.5536 0.82103 0.46466 0.67689 1.61107

12 MCMB 290 290 0.7 37200 25 81.93729 25.79146 77.77224 -145.651 0.96635 0.62749 0.73491 1.82211

Average absolute error: 78.072698 28.821698 68.051659 161.91834 0.8208533 0.511845 0.6336108 1.6674167

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 94

Table A-112: E170 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 240 290 NaN 23140 15 263.4135 -259.651 44.36002 -334.817 0.9069 0.11414 0.89969 1.96562

2 MCMB 290 290 0.7 23140 15 206.9485 20.77247 205.9033 558.3674 2.30839 -2.22366 0.61966 -3.48166

3 MCMB 240 290 NaN 30170 15 166.6486 -161.891 39.5357 -222.792 0.92668 -0.0651 0.92439 1.71634

4 MCMB 290 290 0.7 30170 15 135.9061 22.7987 133.9801 360.0535 2.2695 -2.21352 0.50098 -3.04147

5 MCMB 240 290 NaN 37200 15 109.1556 -106.357 24.55942 -133.694 0.96191 -0.06369 0.9598 1.60175

6 MCMB 290 290 0.7 37200 15 105.5992 13.9541 104.6732 258.1387 2.18805 -2.1308 0.49723 -2.71417

7 MCMB 240 290 NaN 23140 25 461.2687 -457.524 58.65639 -553.159 1.04125 -0.28719 1.00087 1.6743

8 MCMB 290 290 0.7 23140 25 383.6708 136.1792 358.6899 719.8517 3.28286 -3.19752 0.7437 -4.91789

9 MCMB 240 290 NaN 30170 25 300.2541 -298.811 29.40077 -338.684 1.09831 -0.27847 1.06242 -1.75681

10 MCMB 290 290 0.7 30170 25 273.8137 105.2548 252.7753 479.4633 3.10689 -3.06363 0.51663 -4.12641

11 MCMB 240 290 NaN 37200 25 217.6827 -217.028 16.87181 -250.397 1.24285 -0.39882 1.17712 -1.7707

12 MCMB 290 290 0.7 37200 25 205.0641 60.34649 195.9836 337.5417 2.94564 -2.91543 0.4208 -3.50901

Average absolute error: 235.78547 155.04731 122.11579 378.91328 1.8566025 1.4126642 0.7769408 2.6896775

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 95

A.57 E190

Table A-113: E190 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 290 290 0.75 29940 25 102.5733 7.44159 102.30301 -195.41882 1.22244 0.95393 0.76446 2.27138

2 MCMB 250 290 NaN 30200 15 42.31437 13.68093 40.0417 71.73258 0.90743 0.67865 0.60238 1.7529

3 MCMB 290 290 0.75 29970 15 111.93447 -0.59003 111.93291 -302.19755 1.16219 0.23984 1.13718 -3.52885

4 MCMB 250 290 NaN 41000 15 35.14988 14.93836 31.8176 -67.55997 0.87948 0.56014 0.67804 1.49151

5 MCMB 290 290 0.75 40670 15 62.9523 -6.30644 62.63562 -167.71648 1.00563 0.31267 0.95578 -2.06003

6 MCMB 250 290 NaN 51800 15 35.2381 12.15004 33.07719 95.83886 0.99205 0.82039 0.55779 1.95963

7 MCMB 290 290 0.75 51340 15 44.42345 -7.03867 43.86229 -103.35158 1.05304 0.21765 1.0303 2.24066

8 MCMB 250 290 NaN 30200 25 33.93717 -1.81083 33.88882 82.53661 2.41046 2.21638 0.94763 3.82381

9 MCMB 250 290 NaN 41000 25 35.92685 6.66038 35.30408 -77.82526 2.25216 2.17047 0.60106 3.31216

10 MCMB 290 290 0.75 40627 25 67.45424 6.1577 67.1726 130.38613 1.28493 1.02732 0.77179 2.0361

11 MCMB 250 290 NaN 51800 25 30.96081 1.19228 30.93785 83.36852 2.41976 2.32848 0.65836 3.25146

12 MCMB 290 290 0.75 51278 25 54.76432 -16.20313 52.31241 126.22086 1.10188 0.81218 0.74464 2.59821

Average absolute error: 54.802438 7.8475317 53.77384 125.3461 1.3909542 1.028175 0.7874508 2.527225

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 96

Table A-114: E190 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 290 290 0.75 29940 25 280.06426 10.57992 279.86435 459.28425 4.09196 -3.9978 0.8728 -6.27235

2 MCMB 250 290 NaN 30200 15 250.0188 -243.94996 54.75236 -353.05483 0.93291 -0.06276 0.9308 -1.4623

3 MCMB 290 290 0.75 29970 15 228.97826 16.71533 228.36734 728.61658 3.03531 -2.93487 0.77436 -5.35445

4 MCMB 250 290 NaN 41000 15 170.21538 -164.76996 42.70991 -270.33085 0.99233 -0.18128 0.97563 -1.91684

5 MCMB 290 290 0.75 40670 15 144.13061 1.01206 144.12706 414.95986 2.87734 -2.82794 0.5309 -4.17281

6 MCMB 250 290 NaN 51800 15 127.05662 -119.49434 43.17971 -190.89083 0.73667 0.07897 0.73242 -1.23406

7 MCMB 290 290 0.75 51340 15 111.65186 -14.29607 110.73283 267.34613 2.75014 -2.71533 0.43617 -3.69547

8 MCMB 250 290 NaN 30200 25 366.05703 -363.00174 47.19626 -401.20578 1.91125 1.07165 1.58254 3.82381

9 MCMB 250 290 NaN 41000 25 249.23865 -243.20457 54.51093 -361.52924 1.48687 1.02574 1.0764 2.82028

10 MCMB 290 290 0.75 40627 25 218.83257 26.86787 217.17692 395.50507 3.71385 -3.68997 0.42044 -4.79462

11 MCMB 250 290 NaN 51800 25 184.47489 -178.84393 45.23089 -245.05569 1.62885 1.18375 1.11887 3.00233

12 MCMB 290 290 0.75 51278 25 143.01476 -39.33432 137.49921 290.02115 3.48709 -3.47819 0.24901 -4.03507

Average absolute error: 206.14447 118.50584 117.11231 364.81669 2.3037142 1.9373542 0.8083617 3.5486992

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 97

A.58 EA50

Table A-115: EA50 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 167 167 0.46 2719 10 124.52014 -16.39025 123.43673 -317.57757 0.14047 0.00124 0.14046 0.2141

2 MCMB 167 167 0.46 2270 10 72.11528 -0.0766 72.11524 136.35174 0.12322 0.01288 0.12255 0.21629

3 MCMB 167 167 0.46 1818 10 88.50429 -15.82575 87.07787 -135.70483 0.11398 0.02466 0.11128 0.27476

4 MCMB 163 163 0.44 2719 20 69.14703 25.68264 64.20057 132.5849 0.3197 0.28257 0.14955 0.49963

5 MCMB 163 163 0.44 2270 20 80.31067 3.87158 80.2173 141.51122 0.26834 0.23612 0.12749 0.45533

6 MCMB 163 163 0.44 1818 20 113.22851 -21.25965 111.21476 -189.50598 0.26178 0.23769 0.1097 0.43479

Average absolute error: 91.30432 13.851078 89.710412 175.53937 0.2045817 0.1325267 0.1268383 0.34915

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 98

Table A-116: EA50 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 167 167 0.46 2719 10 131.61729 -78.64127 105.53986 -324.20903 0.17628 -0.11762 0.1313 -0.23409

2 MCMB 167 167 0.46 2270 10 88.89321 -63.99209 61.70102 -149.55929 0.18037 -0.12327 0.13167 -0.2337

3 MCMB 167 167 0.46 1818 10 117.76926 -92.96691 72.29629 -195.90191 0.13313 -0.11777 0.06207 -0.22076

4 MCMB 163 163 0.44 2719 20 72.37622 -40.5989 59.917 -123.90962 0.23632 0.09737 0.21533 0.40663

5 MCMB 163 163 0.44 2270 20 101.73289 -69.19986 74.57185 -170.48928 0.26562 0.03353 0.26349 0.41555

6 MCMB 163 163 0.44 1818 20 132.93769 -96.81934 91.09579 -221.37569 0.24851 0.04581 0.24426 0.41569

Average absolute error: 107.55443 73.703062 77.520302 197.57414 0.206705 0.0892283 0.1746867 0.32107

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 99

A.59 F27

Table A-117: F27 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 140 140 0.5 16000 10 83.78791 -11.25394 83.02868 198.07498 1.77877 0.06645 1.77753 4.91986

2 MCMB 140 140 0.5 18000 10 74.52487 -3.18632 74.45673 156.7202 1.46718 0.30669 1.43477 2.54005

3 MCMB 140 140 0.5 20000 10 72.2583 14.22507 70.84426 148.62957 1.38388 0.40376 1.32367 3.9607

4 MCMB 150 150 0.5 16000 10 145.40914 8.74039 145.14622 -322.20208 2.03026 0.87266 1.83315 4.71041

Average absolute error: 93.995055 9.35143 93.368973 206.40671 1.6650225 0.41239 1.59228 4.032755

Table A-118: F27 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 140 140 0.5 16000 10 92.75013 -46.86443 80.03943 -161.37312 1.8345 -0.21156 1.82226 4.7471

2 MCMB 140 140 0.5 18000 10 78.65093 -33.07018 71.36057 -181.08116 1.44892 0.03714 1.44844 2.41462

3 MCMB 140 140 0.5 20000 10 70.25988 -11.65074 69.28717 -155.7348 1.33742 0.15199 1.32876 3.74537

4 MCMB 150 150 0.5 16000 10 143.2653 -26.03717 140.87942 -357.20922 1.91059 0.59813 1.81455 4.42046

Average absolute error: 96.23156 29.40563 90.391648 213.84958 1.6328575 0.249705 1.6035025 3.8318875

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 100

A.60 F50

Table A-119: F50 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 160 160 0.5 14000 10 382.34231 7.7369 382.26402 804.02465 3.16098 -0.0032 3.16098 7.69135

2 MCMB 160 160 0.5 18000 10 397.95019 -7.8821 397.87212 901.04984 4.06392 0.039 4.06373 9.07349

3 MCMB 160 160 0.5 20820 10 309.17755 -15.31422 308.79804 1094.1699 4.35534 0.31403 4.344 15.74983

4 MCMB 160 160 0.5 18000 20 261.78026 -12.83598 261.46537 853.02555 2.87463 0.31826 2.85696 9.70683

Average absolute error: 337.81258 10.9423 337.59989 913.06749 3.6137175 0.1686225 3.6064175 10.555375

Table A-120: F50 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 160 160 0.5 14000 10 371.84785 -57.09225 367.43883 -751.37988 3.17345 -0.27411 3.16159 7.36922

2 MCMB 160 160 0.5 18000 10 386.97757 -55.63999 382.9567 818.03042 4.07518 -0.21668 4.06942 8.83245

3 MCMB 160 160 0.5 20820 10 303.18175 -55.53942 298.05125 1012.7271 4.33648 0.08249 4.3357 15.52699

4 MCMB 160 160 0.5 18000 20 256.62194 -91.49978 239.75531 701.45431 2.92851 -0.12061 2.92602 9.47177

Average absolute error: 329.65728 64.94286 322.05052 820.89793 3.628405 0.1734725 3.6231825 10.300108

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 101

A.61 F70

Table A-121: F70 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 280 0.7 25991 10 68.50255 4.13221 68.37781 157.94415 11.24809 -3.48724 10.69386 -30.05177

2 MCMB 250 280 0.7 33964 10 55.225 3.49051 55.11458 133.40514 12.97212 4.50073 12.16632 39.58197

3 MCMB 250 280 0.7 39985 10 39.82834 -1.56817 39.79746 83.26281 14.5073 5.67311 13.35206 41.02679

4 MCMB 250 280 0.7 33986 20 74.38073 3.46365 74.30004 189.41602 9.92917 3.97151 9.10031 28.95341

Average absolute error: 59.484155 3.163635 59.397473 141.00703 12.16417 4.4081475 11.328138 34.903485

Table A-122: F70 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 280 0.7 25991 10 128.85464 -34.35276 124.19101 207.46308 11.49457 -5.01556 10.34259 -30.16398

2 MCMB 250 280 0.7 33964 10 99.81578 -27.24165 96.02647 168.46908 11.67187 2.49986 11.40102 38.27326

3 MCMB 250 280 0.7 39985 10 78.57967 -28.69585 73.15267 -125.41562 14.34968 4.90418 13.48564 40.49103

4 MCMB 250 280 0.7 33986 20 169.69604 -27.31282 167.4836 302.05745 9.65276 1.87051 9.46979 27.27633

Average absolute error: 119.23653 29.40077 115.21344 200.85131 11.79222 3.5725275 11.17476 34.05115

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 102

A.62 F100

Table A-123: F100 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 280 0.7 34000 10 232.38176 0.93378 232.37988 -460.98202 6.4063 -0.02458 6.40625 14.61953

2 MCMB 250 280 0.7 38000 10 227.32284 -21.71546 226.28326 -609.78395 5.98639 -1.06625 5.89067 13.62168

3 MCMB 250 280 0.7 44000 10 139.72652 30.22109 136.41916 327.70422 5.34332 0.57383 5.31241 13.91516

Average absolute error: 199.81037 17.623443 198.36077 466.15673 5.9120033 0.5548867 5.8697767 14.052123

Table A-124: F100 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 280 0.7 34000 10 247.39745 -24.08865 246.22192 -527.99433 6.51446 -1.42466 6.35677 13.42078

2 MCMB 250 280 0.7 38000 10 238.67525 -41.23945 235.08548 -651.22622 6.34373 -2.46632 5.84467 -13.3877

3 MCMB 250 280 0.7 44000 10 140.50614 14.56033 139.74968 -326.23441 5.53169 -0.82624 5.46964 13.53829

Average absolute error: 208.85961 26.629477 207.01903 501.81832 6.12996 1.5724067 5.89036 13.448923

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 103

A.63 F900

Table A-125: F900 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 300 300 0.8 11000 10 289.33649 -61.39321 282.74808 604.20979 9.02716 2.58254 8.64986 27.12567

2 MCMB 300 300 0.8 15400 10 156.13387 58.97471 144.56752 300.18282 4.06086 0.85894 3.96898 12.15611

3 MCMB 300 300 0.8 20700 10 169.85985 133.57597 104.92772 317.93132 5.36981 1.88814 5.0269 11.98849

4 MCMB 300 300 0.8 15400 20 123.72533 21.70103 121.80731 269.62134 4.5757 2.06463 4.08343 10.64237

Average absolute error: 184.76389 68.91123 163.51266 372.98632 5.7583825 1.8485625 5.4322925 15.47816

Table A-126: F900 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 300 300 0.8 11000 10 327.42224 -52.50641 323.18478 640.15176 8.88599 1.15353 8.8108 26.9451

2 MCMB 300 300 0.8 15400 10 146.86947 55.11408 136.13626 309.06551 3.64201 -0.45567 3.61339 8.80716

3 MCMB 300 300 0.8 20700 10 146.93877 107.25121 100.43994 249.04881 5.1794 0.44821 5.15997 11.89702

4 MCMB 300 300 0.8 15400 20 98.12044 -44.24502 87.57852 -176.86991 2.89566 -0.54296 2.8443 4.33773

Average absolute error: 179.83773 64.77918 161.83488 343.784 5.150765 0.6500925 5.107115 12.996753

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 104

A.64 FA50

Table A-127: FA50 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 260 260 0.72 10450 10 278.71974 -60.57418 272.05783 -399.79898 4.82312 0.00034 4.82312 11.74444

2 MCMB 260 260 0.72 15000 10 148.32979 64.09111 133.76867 273.63193 4.20765 0.70195 4.14869 10.96076

3 MCMB 260 260 0.72 18540 10 184.80347 26.33922 182.91683 -441.59129 3.07503 0.08049 3.07398 8.52125

4 MCMB 260 260 0.72 15000 20 150.72312 4.37047 150.65974 -357.23215 2.85297 0.0867 2.85165 4.44327

Average absolute error: 190.64403 38.843745 184.85077 368.06359 3.7396925 0.21737 3.72436 8.91743

Table A-128: FA50 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 260 260 0.72 10450 10 216.99399 -50.32992 211.07651 -478.36893 5.03843 -1.13214 4.90959 11.66981

2 MCMB 260 260 0.72 15000 10 157.28774 52.84259 148.14551 305.26728 4.04866 -0.23282 4.04196 9.11974

3 MCMB 260 260 0.72 18540 10 185.81759 15.16561 185.19768 -496.44864 3.13124 -0.77875 3.03286 7.23582

4 MCMB 260 260 0.72 15000 20 206.08342 -41.94895 201.76883 -482.67478 3.17545 -1.79219 2.62137 -5.82954

Average absolute error: 191.54569 40.071768 186.54713 440.68991 3.848445 0.983975 3.651445 8.4637275

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 105

A.65 H25A

Table A-129: H25A with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 250 0.63 9843 10 329.52827 1.59602 329.5244 817.16779 6.67973 -0.47069 6.66312 14.32924

2 MCMB 250 250 0.63 8160 10 443.49943 15.52712 443.22754 1085.5273 7.82367 0.69767 7.7925 -17.06262

3 MCMB 250 250 0.63 6350 10 563.22098 12.83901 563.07462 1273.1945 7.09241 1.37858 6.95714 13.37894

4 MCMB 250 250 0.63 6350 20 594.59699 34.55668 593.59196 1176.8965 7.51295 1.49839 7.36201 22.71023

Average absolute error: 482.71142 16.129708 482.35463 1088.1965 7.27719 1.0113325 7.1936925 16.870258

Table A-130: H25A with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 250 0.63 9843 10 292.37797 10.31281 292.19603 734.10785 6.9755 -1.56652 6.79732 14.00096

2 MCMB 250 250 0.63 8160 10 414.34268 28.95812 413.32951 972.6621 7.69927 -0.47512 7.6846 -17.06262

3 MCMB 250 250 0.63 6350 10 527.57687 31.1691 526.65534 1162.2835 6.85954 0.20579 6.85645 12.30634

4 MCMB 250 250 0.63 6350 20 561.75969 136.10308 545.02284 1011.8298 7.50945 -0.49925 7.49284 20.54876

Average absolute error: 449.0143 51.635778 444.30093 970.22081 7.26094 0.68667 7.2078025 15.97967

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 106

A.66 JS32

Table A-131: JS31 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 160 160 0.32 6200 10 71.02965 -3.28872 70.95347 128.29166 0.32237 0.0002 0.32237 0.72839

2 MCMB 160 160 0.32 6200 20 70.42452 20.71884 67.30782 137.01925 0.42209 0.30048 0.29643 0.76616

3 MCMB 160 160 0.32 5000 20 87.6083 -61.21584 62.67244 -154.23875 0.42009 0.25673 0.33251 1.10954

4 MCMB 160 160 0.32 7000 20 81.19423 65.77145 47.60904 155.90551 0.42044 0.37255 0.19487 0.64434

Average absolute error: 77.564175 37.748713 62.135693 143.86379 0.3962475 0.23249 0.286545 0.8121075

Table A-132: JS31 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 160 160 0.32 6200 10 77.04269 -44.96811 62.55754 -134.79428 0.34568 -0.09976 0.33097 -0.60912

2 MCMB 160 160 0.32 6200 20 61.29079 -36.25186 49.42028 -98.52772 0.39188 0.13332 0.3685 0.69833

3 MCMB 160 160 0.32 5000 20 146.08041 -136.86051 51.07532 -199.6416 0.33094 0.08282 0.32041 0.80553

4 MCMB 160 160 0.32 7000 20 38.55956 18.48613 33.83936 91.22065 0.34557 0.27226 0.21282 0.64434

Average absolute error: 80.743363 59.141653 49.223125 131.04606 0.3535175 0.14704 0.308175 0.68933

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 107

A.67 JS41

Table A-133: JS41 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 170 170 0.35 7000 10 96.58584 -18.00754 94.89232 -200.72121 0.48921 -0.01692 0.48892 -1.03135

2 MCMB 170 170 0.35 9000 10 80.98828 14.48129 79.68308 190.66482 0.25168 0.12426 0.21887 0.63532

3 MCMB 170 170 0.35 10500 10 50.5826 1.28725 50.56621 132.09766 0.25076 0.09549 0.23187 -0.48439

4 MCMB 170 170 0.35 9000 20 51.3561 0.86032 51.3489 136.64822 0.38376 0.30652 0.23091 0.7763

Average absolute error: 69.878205 8.6591 69.122628 165.03298 0.3438525 0.1357975 0.2926425 0.73184

Table A-134: JS41 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 170 170 0.35 7000 10 125.79926 -85.05583 92.68743 -305.77421 0.52903 -0.18086 0.49715 -1.03135

2 MCMB 170 170 0.35 9000 10 78.3486 -34.01345 70.58036 -109.99968 0.27504 -0.03969 0.27216 0.63532

3 MCMB 170 170 0.35 10500 10 56.93174 -36.26768 43.88483 -89.35484 0.27472 -0.06846 0.26605 -0.65593

4 MCMB 170 170 0.35 9000 20 93.10548 -72.82786 58.00632 -175.59724 0.27786 0.00538 0.27781 0.54884

Average absolute error: 88.54627 57.041205 66.289735 170.18149 0.3391625 0.0735975 0.3282925 0.71786

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 108

A.68 LJ35

Table A-135: LJ35 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 250 0.7 5000 10 401.77169 -62.46987 396.88538 -1560.6279 1.25852 0.08409 1.25571 -4.54067

2 MCMB 250 250 0.7 6820 10 195.55536 24.08675 194.06629 456.39796 1.08483 0.29387 1.04427 3.41433

3 MCMB 250 250 0.7 8300 10 110.60894 9.49122 110.20097 -238.99638 0.53606 0.13241 0.51945 1.27206

4 MCMB 250 250 0.7 6820 20 150.72456 57.84246 139.18385 -284.4378 0.95893 0.90273 0.32347 1.71433

Average absolute error: 214.66514 38.472575 210.08412 635.11501 0.959585 0.353275 0.785725 2.7353475

Table A-136: LJ35 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 250 0.7 5000 10 442.81394 -150.70656 416.3793 -1738.1363 1.35411 -0.55196 1.23651 -4.54067

2 MCMB 250 250 0.7 6820 10 200.35566 -48.59116 194.37409 -509.05783 1.19073 -0.2604 1.1619 3.41433

3 MCMB 250 250 0.7 8300 10 137.89066 -51.15696 128.04999 -356.86073 0.64283 -0.36376 0.53001 -1.23757

4 MCMB 250 250 0.7 6820 20 204.74589 -61.68225 195.23365 -520.20939 0.65488 0.03565 0.65391 1.25855

Average absolute error: 246.45154 78.034233 233.50926 781.06606 0.9606375 0.3029425 0.8955825 2.61278

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 109

A.69 LJ45

Table A-137: LJ45 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 250 0.7 7000 10 275.47811 -39.50005 272.6315 -939.91165 1.19512 -0.00483 1.19511 -3.08746

2 MCMB 250 250 0.7 8000 10 135.50247 4.77377 135.41836 -303.60477 0.70406 0.11748 0.69419 1.98091

3 MCMB 250 250 0.7 9299 10 164.54062 32.83437 161.23126 -528.62751 0.90826 0.08159 0.90459 2.36553

4 MCMB 250 250 0.7 8000 20 106.70282 -1.32372 106.6946 -259.84535 1.07166 0.60914 0.88171 3.23891

Average absolute error: 170.55601 19.607978 168.99393 507.99732 0.969775 0.20326 0.9189 2.6682025

Table A-138: LJ45 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 250 250 0.7 7000 10 285.8586 -90.55196 271.13739 -1058.1911 1.56572 -0.65247 1.42329 -3.08746

2 MCMB 250 250 0.7 8000 10 147.53119 -40.96592 141.72948 -421.50738 1.15138 -0.47303 1.04973 -2.30537

3 MCMB 250 250 0.7 9299 10 174.96188 -11.46843 174.58561 -617.23266 1.23943 -0.47822 1.14346 -2.35538

4 MCMB 250 250 0.7 8000 20 187.05837 -62.82764 176.19172 -436.72734 1.36333 -0.28025 1.33421 3.07566

Average absolute error: 198.85251 51.453488 190.91105 633.41462 1.329965 0.4709925 1.2376725 2.7059675

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 110

A.70 MD11

Table A-139: MD11 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 330 330 0.82 181623 10 135.669 43.383 128.545 -346.3 5.122 3.165 4.028 9.346

2 MCMB 330 330 0.82 154385 10 135.841 63.037 120.329 258.112 5.131 3.582 3.673 10.306

3 MCMB 330 330 0.82 236125 10 105.76 34.673 99.915 -318.219 5.413 3.872 3.782 9.215

4 MCMB 330 330 0.82 284111 10 46.259 9.744 45.221 -136.247 5.058 3.206 3.912 11.925

5 MCMB 330 330 0.82 154375 20 148.588 20.701 147.139 275.162 4.615 0.786 4.547 9.037

6 MCMB 330 330 0.82 181610 20 143.021 -2.489 142.999 -387.511 4.552 0.694 4.499 8.279

7 MCMB 330 330 0.82 236096 20 81.773 -8.156 81.366 -147.044 5.138 0.527 5.111 10.055

8 MCMB 330 330 0.82 284092 20 66.039 -52.03 40.669 -183.108 4.604 -0.643 4.559 10.142

Average absolute error: 107.86875 29.276625 100.77288 256.46288 4.954125 2.059375 4.263875 9.788125

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 111

Table A-140: MD11 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 330 330 0.82 181623 10 142.343 -22.314 140.583 -341.603 3.811 -2.206 3.108 -8.811

2 MCMB 330 330 0.82 154385 10 152.365 -13.726 151.746 224.435 3.478 -1.784 2.986 -8.084

3 MCMB 330 330 0.82 236125 10 108.273 -20.422 106.329 -321.258 2.921 -1.2 2.664 -6.055

4 MCMB 330 330 0.82 284111 10 60.095 -35.085 48.79 -146.592 3.241 -1.406 2.921 -5.785

5 MCMB 330 330 0.82 154375 20 264.028 -128.323 230.747 -444.835 12.015 -11.634 3.002 -16.8

6 MCMB 330 330 0.82 181610 20 227.317 -128.542 187.483 -366.653 12.129 -11.769 2.931 -18.11

7 MCMB 330 330 0.82 236096 20 164.989 -116.076 117.25 -265.671 11.202 -10.902 2.574 -14.861

8 MCMB 330 330 0.82 284092 20 145.79 -136.695 50.689 -214.857 11.583 -11.263 2.705 -14.6

Average absolute error: 158.15 75.147875 129.20213 290.738 7.5475 6.5205 2.861375 11.63825

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 112

A.71 MD82

Table A-141: MD82 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 310 310 0.74 45404 10 FL>100 86.928 41.758 76.241 179.117 1.61 1.045 1.225 3.29

2 MCMB 310 310 0.74 54483 10 FL>100 79.664 44.473 66.095 166.372 1.572 1.058 1.163 3.389

3 MCMB 310 310 0.74 63559 10 FL>100 74.576 44.204 60.062 152.527 1.62 1.165 1.126 3.166

4 MCMB 310 310 0.74 72633 10 FL>100 73.572 50.546 53.46 142.622 1.739 1.302 1.152 3.119

5 MCMB 310 310 0.74 45402 20 FL>100 100.613 -34.069 94.669 159.167 1.549 -0.591 1.431 -4.816

6 MCMB 310 310 0.74 54480 20 FL>100 81.781 -27.491 77.023 129.417 1.36 -0.507 1.262 -3.239

7 MCMB 310 310 0.74 63555 20 FL>100 67.987 -27.292 62.269 105.114 1.413 -0.541 1.306 -3.237

8 MCMB 310 310 0.74 72627 20 FL>100 53.698 -31.005 43.842 -70.846 1.583 -0.708 1.416 -3.655

9 MCMB 250 250 0.68 45454 10 91.784 -60.869 68.697 -195.316 2.498 -1.455 2.031 -5.351

10 MCMB 250 250 0.68 54545 10 80.268 -47.561 64.66 -193.422 2.439 -1.456 1.957 -4.854

11 MCMB 250 250 0.68 63636 10 67.435 -33.091 58.758 -123.546 2.544 -1.423 2.109 -5.153

12 MCMB 250 250 0.68 72727 10 73.175 -27.177 67.942 -119.938 2.663 -1.518 2.188 -4.829

13 MCMB 250 250 0.68 45454 20 97.923 28.886 93.565 -242.578 1.492 -0.422 1.431 -2.961

14 MCMB 250 250 0.68 54545 20 95.732 18.422 93.943 -237.5 1.656 -0.474 1.587 -5.539

15 MCMB 250 250 0.68 63636 20 79.577 22.859 76.224 -168.988 1.565 -0.322 1.531 -5.564

16 MCMB 250 250 0.68 72727 20 75.588 19.129 73.128 -127.294 1.542 -0.294 1.514 -4.226

Average absolute error: 80.018813 34.927 70.661125 157.11025 1.8028125 0.8925625 1.5268125 4.14925

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 113

Table A-142: MD82 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 310 310 0.74 45404 10 111.549 -13.313 110.752 169.153 1.418 -0.868 1.121 -2.69

2 MCMB 310 310 0.74 54483 10 92.69 0.443 92.689 158.841 1.414 -0.855 1.126 -2.785

3 MCMB 310 310 0.74 63559 10 79.402 7.401 79.056 147.152 1.31 -0.722 1.093 -2.587

4 MCMB 310 310 0.74 72633 10 73.521 16.246 71.703 139.042 0.968 -0.453 0.856 -1.98

5 MCMB 310 310 0.74 45402 20 230.978 -133.42 188.546 -364.585 4.377 -4.317 0.717 -6.556

6 MCMB 310 310 0.74 54480 20 183.443 -105.822 149.843 -292.849 4.26 -4.219 0.59 -5.814

7 MCMB 310 310 0.74 63555 20 149.832 -91.991 118.268 -237.23 4.224 -4.196 0.484 -5.392

8 MCMB 310 310 0.74 72627 20 129.421 -92.206 90.817 -196.902 4.152 -4.098 0.668 -5.395

9 MCMB 250 250 0.68 45454 10 166.448 -156.19 57.53 -276.003 3.765 -2.866 2.441 -6.893

10 MCMB 250 250 0.68 54545 10 130.695 -122.707 44.99 -212.122 3.731 -2.859 2.397 -6.338

11 MCMB 250 250 0.68 63636 10 101.538 -95.15 35.447 -162.133 3.717 -2.721 2.532 -6.695

12 MCMB 250 250 0.68 72727 10 87.846 -76.623 42.962 -150.421 3.81 -2.736 2.651 -6.371

13 MCMB 250 250 0.68 45454 20 199.644 -166.295 110.469 -569.86 3.838 -3.089 2.278 -7.211

14 MCMB 250 250 0.68 54545 20 162.406 -134.206 91.457 -454.911 3.925 -3.147 2.345 -7.489

15 MCMB 250 250 0.68 63636 20 127.544 -102.573 75.804 -369.88 3.458 -2.768 2.072 -5.69

16 MCMB 250 250 0.68 72727 20 104.769 -82.832 64.151 -304.184 3.256 -2.606 1.952 -5.486

Average absolute error: 133.23288 87.338625 89.03025 262.82925 3.2264375 2.6575 1.5826875 5.33575

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 114

A.72 MD83

Table A-143: MD83 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 310 310 0.74 45404 10 FL>100 106.815 37.382 100.06 221.067 2.094 1.262 1.671 5.017

2 MCMB 310 310 0.74 54483 10 FL>100 98.255 45.645 87.009 206.259 2.056 1.197 1.672 4.441

3 MCMB 310 310 0.74 63559 10 FL>100 93.797 45.136 82.223 192.534 2.097 1.123 1.771 4.027

4 MCMB 310 310 0.74 72633 10 FL>100 89.434 47.754 75.618 183.839 2.036 1.348 1.526 4.032

5 MCMB 310 310 0.74 45402 20 FL>100 174.133 -47.047 167.657 249.289 2.986 -1.169 2.748 -6.571

6 MCMB 310 310 0.74 54480 20 FL>100 142.439 -33.439 138.458 210.816 2.91 -1.118 2.687 -5.54

7 MCMB 310 310 0.74 63555 20 FL>100 115.879 -31.727 111.451 186.481 2.771 -1.06 2.56 -4.571

8 MCMB 310 310 0.74 72627 20 FL>100 94.566 -35.996 87.447 139.508 2.928 -1.258 2.644 -4.723

9 MCMB 250 250 0.68 45454 10 103.213 -64.106 80.891 -206.096 2.442 -1.352 2.034 -5.071

10 MCMB 250 250 0.68 54545 10 87.751 -45.286 75.163 -192.345 2.427 -1.381 1.996 -4.387

11 MCMB 250 250 0.68 63636 10 86.455 -35.606 78.782 -243.336 2.435 -1.349 2.027 -4.427

12 MCMB 250 250 0.68 72727 10 78.369 -22.219 75.153 -183.796 2.452 -1.283 2.089 -4.238

13 MCMB 250 250 0.68 45454 20 75.864 43.622 62.069 136.58 1.493 -0.302 1.462 -5.26

14 MCMB 250 250 0.68 54545 20 74.036 35.738 64.839 -148.758 1.252 -0.285 1.219 -2.505

15 MCMB 250 250 0.68 63636 20 78.228 25.585 73.926 -214.517 1.233 -0.242 1.209 -2.448

16 MCMB 250 250 0.68 72727 20 71.003 24.303 66.715 -153.193 1.508 -0.288 1.48 -4.491

Average absolute error: 98.139813 38.786938 89.216313 191.77588 2.195 1.0010625 1.9246875 4.4843125

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 115

Table A-144: MD83 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 310 310 0.74 45404 10 137.163 -32.831 133.176 -193.153 1.699 -0.751 1.524 -3.723

2 MCMB 310 310 0.74 54483 10 113.246 -11.162 112.695 177.033 1.749 -0.816 1.547 -3.833

3 MCMB 310 310 0.74 63559 10 98.235 -1.443 98.224 168.341 1.848 -0.89 1.62 -4.387

4 MCMB 310 310 0.74 72633 10 87.938 7.408 87.625 163.553 1.426 -0.594 1.296 -3.348

5 MCMB 310 310 0.74 45402 20 310.449 -176.736 255.231 -452.077 5.375 -5.173 1.458 -8.296

6 MCMB 310 310 0.74 54480 20 247.728 -137.382 206.144 -363.862 5.304 -5.112 1.414 -7.385

7 MCMB 310 310 0.74 63555 20 199.616 -115.915 162.512 -294.364 5.231 -5.065 1.305 -7.164

8 MCMB 310 310 0.74 72627 20 167.675 -108.549 127.798 -240.814 5.293 -5.118 1.351 -6.843

9 MCMB 250 250 0.68 45454 10 181.912 -170.36 63.792 -295.789 3.759 -2.814 2.492 -6.618

10 MCMB 250 250 0.68 54545 10 140.383 -129.677 53.772 -223.712 3.761 -2.843 2.461 -5.87

11 MCMB 250 250 0.68 63636 10 118.085 -103.656 56.563 -269.916 3.722 -2.77 2.487 -6.037

12 MCMB 250 250 0.68 72727 10 92.826 -77.064 51.747 -209.347 3.581 -2.579 2.484 -5.847

13 MCMB 250 250 0.68 45454 20 193.306 -170.862 90.406 -431.933 3.813 -3.225 2.034 -6.657

14 MCMB 250 250 0.68 54545 20 149.199 -133.345 66.929 -335.901 3.749 -3.218 1.923 -6.987

15 MCMB 250 250 0.68 63636 20 124.454 -109.312 59.495 -264.683 3.627 -3.084 1.909 -6.888

16 MCMB 250 250 0.68 72727 20 94.168 -83.306 43.906 -206.933 3.3 -2.838 1.683 -5.528

Average absolute error: 153.52394 98.063 104.37594 268.21319 3.5773125 2.930625 1.81175 5.9631875

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 116

A.73 P28A

Table A-145: P28A with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 79 79 0.24 1050 10 90.79695 -0.26146 90.79658 -174.27449 0.1148 0.00716 0.11458 0.21667

2 MCMB 79 79 0.24 1050 20 112.63913 1.20555 112.63268 193.84209 0.15174 0.02068 0.15033 0.34235

Average absolute error: 101.71804 0.733505 101.71463 184.05829 0.13327 0.01392 0.132455 0.27951

Table A-146: P28A with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 79 79 0.24 1050 10 88.64124 -12.52992 87.75119 -185.87535 0.1148 0.00716 0.11458 0.21667

2 MCMB 79 79 0.24 1050 20 108.47488 -21.99281 106.22202 159.44579 0.15174 0.02068 0.15033 0.34235

Average absolute error: 98.55806 17.261365 96.986605 172.66057 0.13327 0.01392 0.132455 0.27951

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 117

A.74 PA34

Table A-147: PA34 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 91 91 NaN 2072 10 46.9854 -16.38413 44.03621 -90.0726 0.47325 0.00778 0.47319 0.95345

2 MCMB 91 91 NaN 2072 20 115.27149 -3.32551 115.22351 -230.01292 0.44642 -0.14873 0.42091 0.82012

Average absolute error: 81.128445 9.85482 79.62986 160.04276 0.459835 0.078255 0.44705 0.886785

Table A-148: PA34 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 91 91 NaN 2072 10 83.90818 16.29684 82.31036 -134.61223 0.47325 0.00778 0.47319 0.95345

2 MCMB 91 91 NaN 2072 20 87.93279 34.53785 80.86601 184.53891 0.44642 -0.14873 0.42091 0.82012

Average absolute error: 85.920485 25.417345 81.588185 159.57557 0.459835 0.078255 0.44705 0.886785

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 118

A.75 RJ85

Table A-149: RJ85 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 280 280 0.7 30000 10 245.47646 -72.517 234.52074 -497.59995 10.71629 -2.48927 10.42317 -25.358

2 MCMB 280 280 0.7 38000 10 174.69397 54.88111 165.84947 272.09423 11.54624 2.83494 11.1928 35.3534

3 MCMB 280 280 0.7 44000 10 187.37258 63.70059 176.21214 306.62231 13.28528 3.53409 12.80659 43.06536

4 MCMB 280 280 0.7 38000 20 303.05244 4.00866 303.02592 538.8345 9.37335 2.46572 9.04323 24.1805

Average absolute error: 227.64886 48.77684 219.90207 403.78775 11.23029 2.831005 10.866448 31.989315

Table A-150: RJ85 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 280 280 0.7 30000 10 279.50606 -120.01957 252.42611 -576.16268 10.87321 -3.55549 10.27546 -25.64209

2 MCMB 280 280 0.7 38000 10 128.33779 26.48528 125.57515 -219.12782 11.46206 2.10237 11.2676 33.38698

3 MCMB 280 280 0.7 44000 10 148.73165 41.35106 142.86775 248.74994 13.291 2.83055 12.98609 41.17786

4 MCMB 280 280 0.7 38000 20 228.83063 -30.13614 226.83754 408.05752 9.45245 0.82494 9.41639 20.70859

Average absolute error: 196.35153 54.498013 186.92664 363.02449 11.26968 2.3283375 10.986385 30.22888

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A.76 SB20

Table A-151: SB20 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 190 190 0.5 15000 10 207.52467 -40.21202 203.59146 -463.58939 0.58403 -0.00812 0.58398 -1.22468

2 MCMB 190 190 0.5 19000 10 157.0444 7.15398 156.88137 -302.32206 0.58329 -0.00545 0.58327 -1.20019

3 MCMB 190 190 0.5 23000 10 137.50009 44.15911 130.21616 220.69581 0.58021 -0.00585 0.58018 -1.22125

4 MCMB 190 190 0.5 19000 20 171.31738 -11.86305 170.90615 -357.74655 1.04873 0.25088 1.01828 1.7366

Average absolute error: 168.34664 25.84704 165.39879 336.08845 0.699065 0.067575 0.6914275 1.34568

Table A-152: SB20 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 190 190 0.5 15000 10 214.21316 -127.85208 171.87532 -457.48995 0.69596 -0.23117 0.65645 -1.67818

2 MCMB 190 190 0.5 19000 10 147.22333 -58.79062 134.97545 -305.60198 0.69858 -0.2297 0.65973 -1.65369

3 MCMB 190 190 0.5 23000 10 114.40663 -6.62498 114.21465 -224.26848 0.69344 -0.22883 0.6546 -1.67475

4 MCMB 190 190 0.5 19000 20 165.79211 -122.23908 112.00282 -337.18872 1.23686 -0.12333 1.2307 -2.09951

Average absolute error: 160.40881 78.87669 133.26706 331.13728 0.83121 0.2032575 0.80037 1.7765325

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A.77 SF34

Table A-153: SF34 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 160 150 0.34 12950 20 194.46546 81.55865 176.53612 408.86038 1.16931 0.30788 1.12805 2.60421

2 MCMB 160 150 0.34 10000 20 93.15577 -66.26441 65.47538 -134.27555 0.78034 0.33846 0.70312 2.15894

Average absolute error: 143.81062 73.91153 121.00575 271.56797 0.974825 0.32317 0.915585 2.381575

Table A-154: SF34 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 160 150 0.34 12950 20 166.74399 11.83001 166.3238 320.20505 1.22035 0.11753 1.21468 2.60421

2 MCMB 160 150 0.34 10000 20 177.38783 -166.37387 61.53194 -224.90139 0.67933 0.1481 0.66299 1.81073

Average absolute error: 172.06591 89.10194 113.92787 272.55322 0.94984 0.132815 0.938835 2.20747

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A.78 SH36

Table A-155: SH36 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 140 140 0.32 8300 10 93.6951 -4.61394 93.58143 -157.90879 0.41809 0.09401 0.40738 1.18517

2 MCMB 140 140 0.32 11300 10 66.9368 -9.95161 66.19291 -128.69123 0.42129 0.11258 0.40597 1.18517

3 MCMB 140 140 0.32 12300 10 43.45951 3.45041 43.32232 -73.09018 0.42908 0.17668 0.39101 1.18517

4 MCMB 140 140 0.32 11300 20 64.27375 -2.60013 64.22113 -123.32504 0.36283 0.20473 0.29955 0.73844

Average absolute error: 67.09129 5.1540225 66.829448 120.75381 0.4078225 0.147 0.3759775 1.0734875

Table A-156: SH36 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 140 140 0.32 8300 10 103.92565 -55.64481 87.77354 -198.84063 0.44467 0.01056 0.44455 1.17162

2 MCMB 140 140 0.32 11300 10 74.58699 -41.34799 62.07707 -152.50766 0.44644 0.02913 0.44549 1.17162

3 MCMB 140 140 0.32 12300 10 47.27401 -24.08137 40.68071 -95.31495 0.43894 0.10055 0.42727 1.17162

4 MCMB 140 140 0.32 11300 20 79.67665 -55.06813 57.58359 -162.85285 0.37179 0.04953 0.36847 0.67277

Average absolute error: 76.365825 44.035575 62.028728 152.37902 0.42546 0.0474425 0.421445 1.0469075

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A.79 SW4

Table A-157: SW4 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 160 160 0.35 4600 10 93.27535 -9.16415 92.82408 -137.70895 0.90694 0.07896 0.9035 1.52692

2 MCMB 160 160 0.35 5200 10 138.29362 47.58253 129.85003 295.69148 0.78501 0.30329 0.72405 1.55386

3 MCMB 160 160 0.35 5700 10 98.39969 -41.08568 89.41178 -176.93255 0.45717 0.17013 0.42433 0.84214

4 MCMB 160 160 0.35 5200 20 114.86984 4.26974 114.79046

-

192.87915 0.56237 0.14006 0.54465 0.79879

Average absolute error: 111.20963 25.525525 106.71909 200.80303 0.6778725 0.17311 0.6491325 1.1804275

Table A-158: SW4 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 160 160 0.35 4600 10 128.66746 -64.41895 111.38005 -198.60299 1.01431 -0.05664 1.01273 -1.5679

2 MCMB 160 160 0.35 5200 10 122.59294 29.06368 119.098 234.42537 0.85695 0.30939 0.79915 1.55386

3 MCMB 160 160 0.35 5700 10 118.34227 -66.00478 98.22557 -222.14017 0.40709 0.06151 0.40242 0.64386

4 MCMB 160 160 0.35 5200 20 134.32474 -49.10988 125.02542 -264.93175 0.54388 0.05164 0.54142 -0.85407

Average absolute error: 125.98185 52.149323 113.43226 230.02507 0.7055575 0.119795 0.68893 1.1549225

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A.80 T134

Table A-159: T134 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 270 270 0.74 35000 10 113.46258 -23.87549 110.92213 -208.53125 13.84431 4.79715 12.98661 24.53294

2 MCMB 270 270 0.74 42000 10 150.43193 14.8058 149.70155 347.8841 8.33769 -0.8251 8.29676 -15.99857

3 MCMB 270 270 0.74 47000 10 148.74308 18.54842 147.58205 -270.61518 16.17452 0.16805 16.17365 43.38091

4 MCMB 270 270 0.74 42000 20 121.05463 -1.23377 121.04834 -179.38962 11.65408 1.20789 11.59131 20.95638

Average absolute error: 133.42306 14.61587 132.31352 251.60504 12.50265 1.7495475 12.262083 26.2172

Table A-160: T134 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 270 270 0.74 35000 10 148.62335 -74.88616 128.37821 -293.06236 13.47565 3.15873 13.10021 24.16186

2 MCMB 270 270 0.74 42000 10 151.36568 -32.05716 147.9321 270.47898 8.45054 -2.25205 8.14493 -17.64055

3 MCMB 270 270 0.74 47000 10 141.732 -21.27076 140.12678 -301.6919 15.82035 -1.25889 15.77019 40.32524

4 MCMB 270 270 0.74 42000 20 137.17983 -81.6633 110.22436 -240.41596 11.94092 -1.08258 11.89174 20.61329

Average absolute error: 144.72522 52.469345 131.66536 276.4123 12.421865 1.9380625 12.226768 25.685235

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A.81 T154

Table A-161: T154 with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 297 297 0.8 70000 10 180.62432 32.13834 177.74215 -393.57202 6.31296 -0.37537 6.30179 16.91314

2 MCMB 297 297 0.8 90000 10 122.38321 4.02559 122.31698 -204.75467 5.77451 -0.05693 5.77423 -13.59025

3 MCMB 297 297 0.8 100000 10 95.80163 -32.05158 90.28095 -210.96975 4.49806 -0.67523 4.44709 14.2745

4 MCMB 297 297 0.8 80000 20 101.2742 4.06495 101.19259 192.51669 3.72667 0.36416 3.70884 13.47134

Average absolute error: 125.02084 18.070115 122.88317 250.45328 5.07805 0.3679225 5.0579875 14.562308

Table A-162: T154 with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 297 297 0.8 70000 10 186.92275 4.83708 186.86015 -347.33352 9.0053 -5.75382 6.92741 -16.87035

2 MCMB 297 297 0.8 90000 10 135.29054 -22.49312 133.4076 -240.49411 7.88316 -5.05922 6.04554 -17.81965

3 MCMB 297 297 0.8 100000 10 121.94309 -59.4057 106.49451 -271.42763 7.22492 -5.50054 4.68439 -13.41406

4 MCMB 297 297 0.8 80000 20 178.98266 -28.84868 176.64242 -358.11662 10.64777 -9.18299 5.3896 -17.59742

Average absolute error: 155.78476 28.896145 150.85117 304.34297 8.6902875 6.3741425 5.761735 16.42537

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A.82 TRIN

Table A-163: TRIN with the new atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 90 90 0.35 1335 10 107.73372 -20.45763 105.77353 -181.78623 0.09928 -0.01299 0.09843 0.21218

2 MCMB 90 90 0.35 1335 20 81.35199 1.56651 81.33691 149.5357 0.11008 -0.01309 0.1093 0.21475

3 MCMB 100 100 0.35 1400 10 44.0114 10.02344 42.8548 82.42768 0.12428 0.01978 0.1227 0.31167

Average absolute error: 77.699037 10.682527 76.65508 137.91654 0.1112133 0.0152867 0.1101433 0.2462

Table A-164: TRIN with the old atmosphere model

Rate of climb Fuel flow

ID Phase CAS1 CAS2 mach m ΔT RMS MEAN STD MAX RMS MEAN STD MAX

[knot] [knot] [kg] [K] [ft/min] [ft/min] [ft/min] [ft/min] [kg/min] [kg/min] [kg/min] [kg/min]

1 MCMB 90 90 0.35 1335 10 114.57671 -48.87488 103.62948 -207.6064 0.09928 -0.01299 0.09843 0.21218

2 MCMB 90 90 0.35 1335 20 92.36675 -49.39617 78.04893 -140.19833 0.11008 -0.01309 0.1093 0.21475

3 MCMB 100 100 0.35 1400 10 45.99179 -23.47739 39.54816 -83.37763 0.12428 0.01978 0.1227 0.31167

Average absolute error: 84.31175 40.582813 73.74219 143.72745 0.1112133 0.0152867 0.1101433 0.2462

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Page intentionally left blank

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APPENDIX B: THE NEW BADA ATMOSPHERE MODEL TABLE DATA

This appendix contains table data for the new BADA atmosphere model, i.e. it consists of table data for following initial conditions:

• ISA -20 – temperature deviation -20 from ISA conditions (ΔT = -20 [K]; Δp = 0 [Pa]); • ISA -10 – temperature deviation -10 from ISA conditions (ΔT = -10 [K]; Δp = 0 [Pa]); • ISA – ISA conditions (ΔT = 0; Δp = 0 [Pa]); • ISA 10 – temperature deviation 10 from ISA conditions (ΔT = 10 [K]; Δp = 0 [Pa]); • ISA 20 – temperature deviation 20 from ISA conditions (ΔT = 20 [K]; Δp = 0 [Pa]); • ISA 30 – temperature deviation 30 from ISA conditions (ΔT = 30 [K]; Δp = 0 [Pa]).

The purpose of the appendix is to provide the new BADA atmosphere data which should facilitate the implementation and validation of the new BADA atmosphere model. Temperature (T), pressure (p), density (rho) and speed of sound (a) as the functions of geopotential pressure altitude (flight levels, FL) with the step of 500 ft are provided.

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B.1 THE NEW BADA ATMOSPHERE TABLE DATA FOR ISA -20

Table B-1: ISA -20 table data

FL[-] T[K] p[Pa] rho[kg/m3] a[m/s]

0 268.15 101325 1.316 328.27

5 267.16 99508 1.298 327.67

10 266.17 97717 1.279 327.06

15 265.18 95952 1.261 326.45

20 264.19 94213 1.242 325.84

25 263.2 92500 1.224 325.23

30 262.21 90812 1.207 324.61

35 261.22 89149 1.189 324

40 260.23 87511 1.172 323.38

45 259.23 85897 1.154 322.77

50 258.24 84307 1.137 322.15

55 257.25 82742 1.12 321.53

60 256.26 81200 1.104 320.91

65 255.27 79681 1.087 320.29

70 254.28 78185 1.071 319.67

75 253.29 76713 1.055 319.05

80 252.3 75262 1.039 318.42

85 251.31 73834 1.023 317.8

90 250.32 72428 1.008 317.17

95 249.33 71044 0.993 316.54

100 248.34 69682 0.977 315.91

105 247.35 68340 0.963 315.28

110 246.36 67020 0.948 314.65

115 245.37 65720 0.933 314.02

120 244.38 64441 0.919 313.38

125 243.38 63182 0.904 312.75

130 242.39 61943 0.89 312.11

135 241.4 60724 0.876 311.47

140 240.41 59524 0.863 310.83

145 239.42 58343 0.849 310.19

150 238.43 57182 0.835 309.55

155 237.44 56039 0.822 308.9

160 236.45 54915 0.809 308.26

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FL[-] T[K] p[Pa] rho[kg/m3] a[m/s]

165 235.46 53809 0.796 307.61

170 234.47 52722 0.783 306.96

175 233.48 51652 0.771 306.32

180 232.49 50600 0.758 305.66

185 231.5 49565 0.746 305.01

190 230.51 48548 0.734 304.36

195 229.52 47547 0.722 303.71

200 228.53 46563 0.71 303.05

205 227.54 45596 0.698 302.39

210 226.54 44645 0.687 301.73

215 225.55 43710 0.675 301.07

220 224.56 42791 0.664 300.41

225 223.57 41888 0.653 299.75

230 222.58 41001 0.642 299.08

235 221.59 40128 0.631 298.42

240 220.6 39271 0.62 297.75

245 219.61 38429 0.61 297.08

250 218.62 37601 0.599 296.41

255 217.63 36788 0.589 295.74

260 216.64 35989 0.579 295.06

265 215.65 35204 0.569 294.39

270 214.66 34433 0.559 293.71

275 213.67 33676 0.549 293.03

280 212.68 32932 0.539 292.35

285 211.69 32202 0.53 291.67

290 210.7 31485 0.521 290.99

295 209.7 30781 0.511 290.3

300 208.71 30090 0.502 289.61

305 207.72 29411 0.493 288.93

310 206.73 28745 0.484 288.24

315 205.74 28091 0.476 287.55

320 204.75 27449 0.467 286.85

325 203.76 26819 0.459 286.16

330 202.77 26201 0.45 285.46

335 201.78 25594 0.442 284.76

340 200.79 24999 0.434 284.06

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FL[-] T[K] p[Pa] rho[kg/m3] a[m/s]

345 199.8 24415 0.426 283.36

350 198.81 23842 0.418 282.66

355 197.82 23280 0.41 281.95

360 196.83 22729 0.402 281.25

365 196.65 22190 0.393 281.12

370 196.65 21663 0.384 281.12

375 196.65 21148 0.375 281.12

380 196.65 20646 0.366 281.12

385 196.65 20156 0.357 281.12

390 196.65 19677 0.349 281.12

395 196.65 19210 0.34 281.12

400 196.65 18754 0.332 281.12

405 196.65 18309 0.324 281.12

410 196.65 17874 0.317 281.12

415 196.65 17449 0.309 281.12

420 196.65 17035 0.302 281.12

425 196.65 16631 0.295 281.12

430 196.65 16236 0.288 281.12

435 196.65 15850 0.281 281.12

440 196.65 15474 0.274 281.12

445 196.65 15106 0.268 281.12

450 196.65 14748 0.261 281.12

455 196.65 14397 0.255 281.12

460 196.65 14056 0.249 281.12

465 196.65 13722 0.243 281.12

470 196.65 13396 0.237 281.12

475 196.65 13078 0.232 281.12

480 196.65 12767 0.226 281.12

485 196.65 12464 0.221 281.12

490 196.65 12168 0.216 281.12

495 196.65 11879 0.21 281.12

500 196.65 11597 0.205 281.12

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B.2 THE NEW BADA ATMOSPHERE TABLE DATA FOR ISA -10

Table B-2: ISA -10 table data

FL[-] T[K] p[Pa] rho[kg/m3] a[m/s]

0 278.15 101325 1.269 334.34

5 277.16 99508 1.251 333.74

10 276.17 97717 1.233 333.14

15 275.18 95952 1.215 332.55

20 274.19 94213 1.197 331.95

25 273.2 92500 1.18 331.35

30 272.21 90812 1.162 330.75

35 271.22 89149 1.145 330.14

40 270.23 87511 1.128 329.54

45 269.23 85897 1.111 328.94

50 268.24 84307 1.095 328.33

55 267.25 82742 1.079 327.72

60 266.26 81200 1.062 327.11

65 265.27 79681 1.046 326.51

70 264.28 78185 1.031 325.9

75 263.29 76713 1.015 325.28

80 262.3 75262 1 324.67

85 261.31 73834 0.984 324.06

90 260.32 72428 0.969 323.44

95 259.33 71044 0.954 322.83

100 258.34 69682 0.94 322.21

105 257.35 68340 0.925 321.59

110 256.36 67020 0.911 320.97

115 255.37 65720 0.897 320.35

120 254.38 64441 0.883 319.73

125 253.38 63182 0.869 319.11

130 252.39 61943 0.855 318.48

135 251.4 60724 0.841 317.86

140 250.41 59524 0.828 317.23

145 249.42 58343 0.815 316.6

150 248.43 57182 0.802 315.97

155 247.44 56039 0.789 315.34

160 246.45 54915 0.776 314.71

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 132

FL[-] T[K] p[Pa] rho[kg/m3] a[m/s]

165 245.46 53809 0.764 314.08

170 244.47 52722 0.751 313.44

175 243.48 51652 0.739 312.81

180 242.49 50600 0.727 312.17

185 241.5 49565 0.715 311.53

190 240.51 48548 0.703 310.89

195 239.52 47547 0.692 310.25

200 238.53 46563 0.68 309.61

205 237.54 45596 0.669 308.96

210 236.54 44645 0.658 308.32

215 235.55 43710 0.646 307.67

220 234.56 42791 0.636 307.03

225 233.57 41888 0.625 306.38

230 232.58 41001 0.614 305.73

235 231.59 40128 0.604 305.07

240 230.6 39271 0.593 304.42

245 229.61 38429 0.583 303.77

250 228.62 37601 0.573 303.11

255 227.63 36788 0.563 302.45

260 226.64 35989 0.553 301.8

265 225.65 35204 0.543 301.13

270 224.66 34433 0.534 300.47

275 223.67 33676 0.525 299.81

280 222.68 32932 0.515 299.15

285 221.69 32202 0.506 298.48

290 220.7 31485 0.497 297.81

295 219.7 30781 0.488 297.14

300 218.71 30090 0.479 296.47

305 217.72 29411 0.471 295.8

310 216.73 28745 0.462 295.13

315 215.74 28091 0.454 294.45

320 214.75 27449 0.445 293.77

325 213.76 26819 0.437 293.1

330 212.77 26201 0.429 292.42

335 211.78 25594 0.421 291.73

340 210.79 24999 0.413 291.05

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 133

FL[-] T[K] p[Pa] rho[kg/m3] a[m/s]

345 209.8 24415 0.405 290.37

350 208.81 23842 0.398 289.68

355 207.82 23280 0.39 288.99

360 206.83 22729 0.383 288.3

365 206.65 22190 0.374 288.18

370 206.65 21663 0.365 288.18

375 206.65 21148 0.357 288.18

380 206.65 20646 0.348 288.18

385 206.65 20156 0.34 288.18

390 206.65 19677 0.332 288.18

395 206.65 19210 0.324 288.18

400 206.65 18754 0.316 288.18

405 206.65 18309 0.309 288.18

410 206.65 17874 0.301 288.18

415 206.65 17449 0.294 288.18

420 206.65 17035 0.287 288.18

425 206.65 16631 0.28 288.18

430 206.65 16236 0.274 288.18

435 206.65 15850 0.267 288.18

440 206.65 15474 0.261 288.18

445 206.65 15106 0.255 288.18

450 206.65 14748 0.249 288.18

455 206.65 14397 0.243 288.18

460 206.65 14056 0.237 288.18

465 206.65 13722 0.231 288.18

470 206.65 13396 0.226 288.18

475 206.65 13078 0.22 288.18

480 206.65 12767 0.215 288.18

485 206.65 12464 0.21 288.18

490 206.65 12168 0.205 288.18

495 206.65 11879 0.2 288.18

500 206.65 11597 0.196 288.18

Page 150: EUROCONTROL · 2019-02-18 · The information contained in this document may not be modified without prior written permission from EUROCONTROL. EUROCONTROL makes no warranty, either

EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 134

B.3 THE NEW BADA ATMOSPHERE TABLE DATA FOR ISA

Table B-3: ISA table data

FL[-] T[K] p[Pa] rho[kg/m3] a[m/s]

0 288.15 101325 1.225 340.29

5 287.16 99508 1.207 339.71

10 286.17 97717 1.19 339.12

15 285.18 95952 1.172 338.53

20 284.19 94213 1.155 337.95

25 283.2 92500 1.138 337.36

30 282.21 90812 1.121 336.77

35 281.22 89149 1.104 336.17

40 280.23 87511 1.088 335.58

45 279.23 85897 1.072 334.99

50 278.24 84307 1.056 334.39

55 277.25 82742 1.04 333.8

60 276.26 81200 1.024 333.2

65 275.27 79681 1.008 332.6

70 274.28 78185 0.993 332

75 273.29 76713 0.978 331.4

80 272.3 75262 0.963 330.8

85 271.31 73834 0.948 330.2

90 270.32 72428 0.933 329.6

95 269.33 71044 0.919 328.99

100 268.34 69682 0.905 328.39

105 267.35 68340 0.891 327.78

110 266.36 67020 0.877 327.17

115 265.37 65720 0.863 326.56

120 264.38 64441 0.849 325.95

125 263.38 63182 0.836 325.34

130 262.39 61943 0.822 324.73

135 261.4 60724 0.809 324.12

140 260.41 59524 0.796 323.5

145 259.42 58343 0.783 322.89

150 258.43 57182 0.771 322.27

155 257.44 56039 0.758 321.65

160 256.45 54915 0.746 321.03

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 135

FL[-] T[K] p[Pa] rho[kg/m3] a[m/s]

165 255.46 53809 0.734 320.41

170 254.47 52722 0.722 319.79

175 253.48 51652 0.71 319.17

180 252.49 50600 0.698 318.54

185 251.5 49565 0.687 317.92

190 250.51 48548 0.675 317.29

195 249.52 47547 0.664 316.66

200 248.53 46563 0.653 316.03

205 247.54 45596 0.642 315.4

210 246.54 44645 0.631 314.77

215 245.55 43710 0.62 314.14

220 244.56 42791 0.61 313.5

225 243.57 41888 0.599 312.87

230 242.58 41001 0.589 312.23

235 241.59 40128 0.579 311.59

240 240.6 39271 0.569 310.95

245 239.61 38429 0.559 310.31

250 238.62 37601 0.549 309.67

255 237.63 36788 0.539 309.03

260 236.64 35989 0.53 308.38

265 235.65 35204 0.52 307.74

270 234.66 34433 0.511 307.09

275 233.67 33676 0.502 306.44

280 232.68 32932 0.493 305.79

285 231.69 32202 0.484 305.14

290 230.7 31485 0.475 304.48

295 229.7 30781 0.467 303.83

300 228.71 30090 0.458 303.17

305 227.72 29411 0.45 302.52

310 226.73 28745 0.442 301.86

315 225.74 28091 0.433 301.2

320 224.75 27449 0.425 300.54

325 223.76 26819 0.418 299.87

330 222.77 26201 0.41 299.21

335 221.78 25594 0.402 298.54

340 220.79 24999 0.394 297.87

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 136

FL[-] T[K] p[Pa] rho[kg/m3] a[m/s]

345 219.8 24415 0.387 297.21

350 218.81 23842 0.38 296.54

355 217.82 23280 0.372 295.86

360 216.83 22729 0.365 295.19

365 216.65 22190 0.357 295.07

370 216.65 21663 0.348 295.07

375 216.65 21148 0.34 295.07

380 216.65 20646 0.332 295.07

385 216.65 20156 0.324 295.07

390 216.65 19677 0.316 295.07

395 216.65 19210 0.309 295.07

400 216.65 18754 0.302 295.07

405 216.65 18309 0.294 295.07

410 216.65 17874 0.287 295.07

415 216.65 17449 0.281 295.07

420 216.65 17035 0.274 295.07

425 216.65 16631 0.267 295.07

430 216.65 16236 0.261 295.07

435 216.65 15850 0.255 295.07

440 216.65 15474 0.249 295.07

445 216.65 15106 0.243 295.07

450 216.65 14748 0.237 295.07

455 216.65 14397 0.232 295.07

460 216.65 14056 0.226 295.07

465 216.65 13722 0.221 295.07

470 216.65 13396 0.215 295.07

475 216.65 13078 0.21 295.07

480 216.65 12767 0.205 295.07

485 216.65 12464 0.2 295.07

490 216.65 12168 0.196 295.07

495 216.65 11879 0.191 295.07

500 216.65 11597 0.186 295.07

Page 153: EUROCONTROL · 2019-02-18 · The information contained in this document may not be modified without prior written permission from EUROCONTROL. EUROCONTROL makes no warranty, either

Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 137

B.4 THE NEW BADA ATMOSPHERE TABLE DATA FOR ISA+10

Table B-4: ISA+10 table data

FL[-] T[K] p[Pa] rho[kg/m3] a[m/s]

0 298.15 101325 1.184 346.15

5 297.16 99508 1.167 345.57

10 296.17 97717 1.149 345

15 295.18 95952 1.132 344.42

20 294.19 94213 1.116 343.84

25 293.2 92500 1.099 343.26

30 292.21 90812 1.083 342.68

35 291.22 89149 1.066 342.1

40 290.23 87511 1.05 341.52

45 289.23 85897 1.035 340.93

50 288.24 84307 1.019 340.35

55 287.25 82742 1.003 339.76

60 286.26 81200 0.988 339.18

65 285.27 79681 0.973 338.59

70 284.28 78185 0.958 338

75 283.29 76713 0.943 337.41

80 282.3 75262 0.929 336.82

85 281.31 73834 0.914 336.23

90 280.32 72428 0.9 335.64

95 279.33 71044 0.886 335.04

100 278.34 69682 0.872 334.45

105 277.35 68340 0.858 333.85

110 276.36 67020 0.845 333.26

115 275.37 65720 0.831 332.66

120 274.38 64441 0.818 332.06

125 273.38 63182 0.805 331.46

130 272.39 61943 0.792 330.86

135 271.4 60724 0.779 330.26

140 270.41 59524 0.767 329.65

145 269.42 58343 0.754 329.05

150 268.43 57182 0.742 328.44

155 267.44 56039 0.73 327.84

160 266.45 54915 0.718 327.23

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 138

FL[-] T[K] p[Pa] rho[kg/m3] a[m/s]

165 265.46 53809 0.706 326.62

170 264.47 52722 0.694 326.01

175 263.48 51652 0.683 325.4

180 262.49 50600 0.672 324.79

185 261.5 49565 0.66 324.17

190 260.51 48548 0.649 323.56

195 259.52 47547 0.638 322.94

200 258.53 46563 0.627 322.33

205 257.54 45596 0.617 321.71

210 256.54 44645 0.606 321.09

215 255.55 43710 0.596 320.47

220 254.56 42791 0.586 319.85

225 253.57 41888 0.575 319.22

230 252.58 41001 0.565 318.6

235 251.59 40128 0.556 317.98

240 250.6 39271 0.546 317.35

245 249.61 38429 0.536 316.72

250 248.62 37601 0.527 316.09

255 247.63 36788 0.518 315.46

260 246.64 35989 0.508 314.83

265 245.65 35204 0.499 314.2

270 244.66 34433 0.49 313.56

275 243.67 33676 0.481 312.93

280 242.68 32932 0.473 312.29

285 241.69 32202 0.464 311.65

290 240.7 31485 0.456 311.01

295 239.7 30781 0.447 310.37

300 238.71 30090 0.439 309.73

305 237.72 29411 0.431 309.09

310 236.73 28745 0.423 308.44

315 235.74 28091 0.415 307.8

320 234.75 27449 0.407 307.15

325 233.76 26819 0.4 306.5

330 232.77 26201 0.392 305.85

335 231.78 25594 0.385 305.2

340 230.79 24999 0.377 304.55

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 139

FL[-] T[K] p[Pa] rho[kg/m3] a[m/s]

345 229.8 24415 0.37 303.89

350 228.81 23842 0.363 303.24

355 227.82 23280 0.356 302.58

360 226.83 22729 0.349 301.92

365 226.65 22190 0.341 301.8

370 226.65 21663 0.333 301.8

375 226.65 21148 0.325 301.8

380 226.65 20646 0.317 301.8

385 226.65 20156 0.31 301.8

390 226.65 19677 0.302 301.8

395 226.65 19210 0.295 301.8

400 226.65 18754 0.288 301.8

405 226.65 18309 0.281 301.8

410 226.65 17874 0.275 301.8

415 226.65 17449 0.268 301.8

420 226.65 17035 0.262 301.8

425 226.65 16631 0.256 301.8

430 226.65 16236 0.25 301.8

435 226.65 15850 0.244 301.8

440 226.65 15474 0.238 301.8

445 226.65 15106 0.232 301.8

450 226.65 14748 0.227 301.8

455 226.65 14397 0.221 301.8

460 226.65 14056 0.216 301.8

465 226.65 13722 0.211 301.8

470 226.65 13396 0.206 301.8

475 226.65 13078 0.201 301.8

480 226.65 12767 0.196 301.8

485 226.65 12464 0.192 301.8

490 226.65 12168 0.187 301.8

495 226.65 11879 0.183 301.8

500 226.65 11597 0.178 301.8

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 140

B.5 THE NEW BADA ATMOSPHERE TABLE DATA FOR ISA+20

Table B-5: ISA+20 table data

FL[-] T[K] p[Pa] rho[kg/m3] a[m/s]

0 308.15 101325 1.145 351.91

5 307.16 99508 1.129 351.34

10 306.17 97717 1.112 350.77

15 305.18 95952 1.095 350.2

20 304.19 94213 1.079 349.64

25 303.2 92500 1.063 349.07

30 302.21 90812 1.047 348.5

35 301.22 89149 1.031 347.92

40 300.23 87511 1.015 347.35

45 299.23 85897 1 346.78

50 298.24 84307 0.985 346.2

55 297.25 82742 0.97 345.63

60 296.26 81200 0.955 345.05

65 295.27 79681 0.94 344.47

70 294.28 78185 0.926 343.9

75 293.29 76713 0.911 343.32

80 292.3 75262 0.897 342.74

85 291.31 73834 0.883 342.15

90 290.32 72428 0.869 341.57

95 289.33 71044 0.855 340.99

100 288.34 69682 0.842 340.4

105 287.35 68340 0.829 339.82

110 286.36 67020 0.815 339.23

115 285.37 65720 0.802 338.65

120 284.38 64441 0.789 338.06

125 283.38 63182 0.777 337.47

130 282.39 61943 0.764 336.88

135 281.4 60724 0.752 336.29

140 280.41 59524 0.739 335.69

145 279.42 58343 0.727 335.1

150 278.43 57182 0.715 334.51

155 277.44 56039 0.704 333.91

160 276.45 54915 0.692 333.31

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 141

FL[-] T[K] p[Pa] rho[kg/m3] a[m/s]

165 275.46 53809 0.681 332.72

170 274.47 52722 0.669 332.12

175 273.48 51652 0.658 331.52

180 272.49 50600 0.647 330.92

185 271.5 49565 0.636 330.31

190 270.51 48548 0.625 329.71

195 269.52 47547 0.615 329.11

200 268.53 46563 0.604 328.5

205 267.54 45596 0.594 327.9

210 266.54 44645 0.584 327.29

215 265.55 43710 0.573 326.68

220 264.56 42791 0.563 326.07

225 263.57 41888 0.554 325.46

230 262.58 41001 0.544 324.85

235 261.59 40128 0.534 324.23

240 260.6 39271 0.525 323.62

245 259.61 38429 0.516 323

250 258.62 37601 0.506 322.39

255 257.63 36788 0.497 321.77

260 256.64 35989 0.489 321.15

265 255.65 35204 0.48 320.53

270 254.66 34433 0.471 319.91

275 253.67 33676 0.462 319.28

280 252.68 32932 0.454 318.66

285 251.69 32202 0.446 318.03

290 250.7 31485 0.438 317.41

295 249.7 30781 0.429 316.78

300 248.71 30090 0.421 316.15

305 247.72 29411 0.414 315.52

310 246.73 28745 0.406 314.89

315 245.74 28091 0.398 314.26

320 244.75 27449 0.391 313.62

325 243.76 26819 0.383 312.99

330 242.77 26201 0.376 312.35

335 241.78 25594 0.369 311.71

340 240.79 24999 0.362 311.07

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 142

FL[-] T[K] p[Pa] rho[kg/m3] a[m/s]

345 239.8 24415 0.355 310.43

350 238.81 23842 0.348 309.79

355 237.82 23280 0.341 309.15

360 236.83 22729 0.334 308.5

365 236.65 22190 0.327 308.39

370 236.65 21663 0.319 308.39

375 236.65 21148 0.311 308.39

380 236.65 20646 0.304 308.39

385 236.65 20156 0.297 308.39

390 236.65 19677 0.29 308.39

395 236.65 19210 0.283 308.39

400 236.65 18754 0.276 308.39

405 236.65 18309 0.27 308.39

410 236.65 17874 0.263 308.39

415 236.65 17449 0.257 308.39

420 236.65 17035 0.251 308.39

425 236.65 16631 0.245 308.39

430 236.65 16236 0.239 308.39

435 236.65 15850 0.233 308.39

440 236.65 15474 0.228 308.39

445 236.65 15106 0.222 308.39

450 236.65 14748 0.217 308.39

455 236.65 14397 0.212 308.39

460 236.65 14056 0.207 308.39

465 236.65 13722 0.202 308.39

470 236.65 13396 0.197 308.39

475 236.65 13078 0.193 308.39

480 236.65 12767 0.188 308.39

485 236.65 12464 0.183 308.39

490 236.65 12168 0.179 308.39

495 236.65 11879 0.175 308.39

500 236.65 11597 0.171 308.39

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 143

B.6 THE NEW BADA ATMOSPHERE TABLE DATA FOR ISA+30

Table B-6: ISA+30 table data

FL[-] T[K] p[Pa] rho[kg/m3] a[m/s]

0 318.15 101325 1.109 357.57

5 317.16 99508 1.093 357.01

10 316.17 97717 1.077 356.45

15 315.18 95952 1.061 355.9

20 314.19 94213 1.045 355.34

25 313.2 92500 1.029 354.78

30 312.21 90812 1.013 354.21

35 311.22 89149 0.998 353.65

40 310.23 87511 0.983 353.09

45 309.23 85897 0.968 352.52

50 308.24 84307 0.953 351.96

55 307.25 82742 0.938 351.39

60 306.26 81200 0.924 350.83

65 305.27 79681 0.909 350.26

70 304.28 78185 0.895 349.69

75 303.29 76713 0.881 349.12

80 302.3 75262 0.867 348.55

85 301.31 73834 0.854 347.98

90 300.32 72428 0.84 347.41

95 299.33 71044 0.827 346.83

100 298.34 69682 0.814 346.26

105 297.35 68340 0.801 345.68

110 296.36 67020 0.788 345.11

115 295.37 65720 0.775 344.53

120 294.38 64441 0.763 343.95

125 293.38 63182 0.75 343.37

130 292.39 61943 0.738 342.79

135 291.4 60724 0.726 342.21

140 290.41 59524 0.714 341.63

145 289.42 58343 0.702 341.04

150 288.43 57182 0.691 340.46

155 287.44 56039 0.679 339.88

160 286.45 54915 0.668 339.29

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 144

FL[-] T[K] p[Pa] rho[kg/m3] a[m/s]

165 285.46 53809 0.657 338.7

170 284.47 52722 0.646 338.11

175 283.48 51652 0.635 337.52

180 282.49 50600 0.624 336.93

185 281.5 49565 0.613 336.34

190 280.51 48548 0.603 335.75

195 279.52 47547 0.593 335.16

200 278.53 46563 0.582 334.56

205 277.54 45596 0.572 333.97

210 276.54 44645 0.562 333.37

215 275.55 43710 0.553 332.77

220 274.56 42791 0.543 332.17

225 273.57 41888 0.533 331.57

230 272.58 41001 0.524 330.97

235 271.59 40128 0.515 330.37

240 270.6 39271 0.506 329.77

245 269.61 38429 0.497 329.16

250 268.62 37601 0.488 328.56

255 267.63 36788 0.479 327.95

260 266.64 35989 0.47 327.35

265 265.65 35204 0.462 326.74

270 264.66 34433 0.453 326.13

275 263.67 33676 0.445 325.52

280 262.68 32932 0.437 324.9

285 261.69 32202 0.429 324.29

290 260.7 31485 0.421 323.68

295 259.7 30781 0.413 323.06

300 258.71 30090 0.405 322.44

305 257.72 29411 0.398 321.83

310 256.73 28745 0.39 321.21

315 255.74 28091 0.383 320.59

320 254.75 27449 0.375 319.97

325 253.76 26819 0.368 319.34

330 252.77 26201 0.361 318.72

335 251.78 25594 0.354 318.09

340 250.79 24999 0.347 317.47

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Revision of Atmosphere Model in BADA Aircraft Performance Model EUROCONTROL

Project: BADA – EEC Technical/Scientific Report No. 2010-01 145

FL[-] T[K] p[Pa] rho[kg/m3] a[m/s]

345 249.8 24415 0.34 316.84

350 248.81 23842 0.334 316.21

355 247.82 23280 0.327 315.58

360 246.83 22729 0.321 314.95

365 246.65 22190 0.313 314.84

370 246.65 21663 0.306 314.84

375 246.65 21148 0.299 314.84

380 246.65 20646 0.292 314.84

385 246.65 20156 0.285 314.84

390 246.65 19677 0.278 314.84

395 246.65 19210 0.271 314.84

400 246.65 18754 0.265 314.84

405 246.65 18309 0.259 314.84

410 246.65 17874 0.252 314.84

415 246.65 17449 0.246 314.84

420 246.65 17035 0.241 314.84

425 246.65 16631 0.235 314.84

430 246.65 16236 0.229 314.84

435 246.65 15850 0.224 314.84

440 246.65 15474 0.219 314.84

445 246.65 15106 0.213 314.84

450 246.65 14748 0.208 314.84

455 246.65 14397 0.203 314.84

460 246.65 14056 0.199 314.84

465 246.65 13722 0.194 314.84

470 246.65 13396 0.189 314.84

475 246.65 13078 0.185 314.84

480 246.65 12767 0.18 314.84

485 246.65 12464 0.176 314.84

490 246.65 12168 0.172 314.84

495 246.65 11879 0.168 314.84

500 246.65 11597 0.164 314.84

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EUROCONTROL Revision of Atmosphere Model in BADA Aircraft Performance Model

Project: BADA – EEC Technical/Scientific Report No. 2010-01 146

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