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PILOTS OPERATING HANDBOOK

KADET SENIOR: 2013 UAV

ADAPTATION

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This POH includes the main characteristics of the KADET SENIOR UAV and theperformance aspects of the aircraft.

The data for the KADET SENIOR analytical calculations, plots and tables described on thisHandbook are based on the adaptation made by Universidad de San Buenaventura Bogot

on 2013.

All the specifications and data given on this Handbook are made by Universidad de SanBuenaventura Bogot students at the Aeronautical Engineering Program.

Authors:Eng. St. Juan Jos Sandoval SoteloEng. St. Marlon Gabriel Rincn MorenoEng. St. Fabio Andrs Sierra JimnezEng. St. Luis Felipe Ibaez PachnEng. St. Andrs Felipe Rodrguez ChaparroEng. St. Laura Alejandra Pea FeoEng. St. Jess Andrs Vega Moreno

This version is made only for academic purposes. Data obtained on this Handbook must be

confirmed by experimental tests. The authors mentioned previously have no relation withSIG Model Airplane Company. Commercial distribution of this document is prohibited.

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PILOTS OPERATING HANDBOOK

KADET SENIORUnmanned Aerial Vehicle Adaptation

Bogot, Colombia

2013

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PERFORMANCE- SPECIFICATIONS

SPEED

Maximum at sea level 75,04 Knots 38,6051m/s 116,81 Ft/s

Cruise, 75% Power at 5000 ft. 64,66 Knots 33,268 m/s 109,14 Ft/s

CRUISE (75% Power at 5000 ft.)

Range 28,306 Km 15,28 NM

Time 14,2 min at constant speed.

Speed 64,66 Knots 33,268 m/s 109,14 Ft/s

OPTIMAL RANGE

Range (For minimum Drag Speed) 105,45 Km 56 NM

Time 103,8 min at constant speed

Speed 33,14 Knots 17,05 m/s 55,9 ft/s

CLIMBMaximum Rate of Climb at sea level 1700,7 fpm 8,64 m/s 28,34 Ft/s

SERVICE CEILING 15110 Ft 4605,52 m

TAKE OFF PERFORMANCE

Ground Roll at Sea Level 130 m 426,5 ftTotal Distance (For 15 m obstacle height) 191,94 m 630 ft

LANDING PERFORMANCEGround Roll at Sea Level 195 m 639,76 Ft

Total Distance (For 15 m obstacle height) 485 m 1591,2 Ft

STALL SPEED AT SEA LEVEL 20.29 Knots 10.44 m/s 32,26 ft

STANDARD EMPTY WEIGHT 3,28 Kg. 32,16 N. 7,24 Lb

BATTERYVoltage 22.2 V

Current/Time 5000 mAh

ENGINE AXI 4120/18PROPELLER. Fixed Pitch, Diameter 356 mm 14 in

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TABLE OF CONTENTS

GENERAL...6- Three View- Introduction- Descriptive Data- Symbols, Abbreviations and Terminology

LIMITATIONS9- Introduction- Airspeed Limitations- Power Plant Limitations- Center of Gravity Limits- Flight Load Factor Limits- Kind of Operation Limits- Battery Limitations

PERFORMANCE11- Airspeed Calibration- Temperature Conversion Chart- Density Altitude Chart- Stall Speeds- Take off Parameters- Rate of Climb- Time and Distance on Climb

-

Maximum Climb Angle- Cruise Parameters- Range- Gliding- Landing

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SECTION : GENERAL

Figure 1-1. Three View

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Introduction

This Handbook contains 3 sections about general description, limitations and performanceof the UAV. On this section the basic data of the aircraft is provided, with some information

of interest about the propulsive and structural components. Also symbols, abbreviationsand terminology are located at the end of this section.

Descriptive Data

ENGINENumber of Engines.1Engine Manufacturer.Model Motors S.R.O. Czech RepublicEngine Model Number.AXI 4120/18 Gold LineEngine Type. 320 g, Electric Neodymium Magnets Motor. 6 mm Shaft Diameter. 515RPM/V.

Engine Rated Power.1000 Watts1,34 HP

PROPELLERPropeller Manufacturer.APC PropellersPropeller Model Number.14x10 Thin Electric PropellerPropeller Type.Fixed PitchNumber of Blades.2Diameter.14 in356 mmPitch.10 in254 mm

BATTERYNumber of Batteries.2

Voltage.22 VCapacity.5000 mAhWeight.0,75 Kg each

MAXIMUM CERTIFICATED WEIGHTSTakeoff and Landing.7,000 Kg. 68,65 N. 15,432 Lb. 0,4798 Slug.Delivery Operational UAV Weight.4,78 Kg. 46,87 N. 10,55 Lb. 0,327 SlugWeight in Equipment. 2 kg. 19,61 N. 4,4147 Lb. 0,137 Slug.

STANDARD EMPTY WEIGHTSOperational Empty Weight.3,28 Kg. 32,16 N. 7,24 Lb. 0,2247 Slug.Engine Weight. 0,32 Kg. 3,13 N. 0,706 Lb. 0,021 SlugStructure Weight. 2,2 Kg. 21,5 N. 4,856 Lb. 0,15 Slug.UAV Equipment. 1,88 Kg. 18,43 N. 4,15 Lb. 0,128 Slug.

NOTE:Delivery Operational UAV Weight includes Operational Empty Weight and 2 BatteriesWeight. On OEW some equipment of the UAV configuration are included (like mainelectronic systems, engine, antennas, cameras, sensors and other devices), so they mustntbe taken in account in the 2 Kg Equipment Weight. This Equipment Weight is available forcustomers extra devices.

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SPECIFIC LOADINGSWing Loading. 92,52 N/m2. 1,934 Lb/Ft2Power Loading. 0,09807 N/W. 14,39 Lb/HP

Symbols, Abbreviation and Terminology

GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS

KCAS. Knots Calibrated Airspeed. Its the indicated airspeed corrected for positionand instruments. Its the same KTAS at sea level, using ISA conditions.KIAS. Knots Indicated Airspeed. Its the speed indicated by the instrument,expressed in Knots.

KTAS. Knots True Airspeed. Its the real speed of the Aircraft in the air. Its expressedin Knots.VA Maneuvering Speed. Maximum speed for abrupt control travel.VNO. Maximum Structural Cruising Speed.Its the speed that should not be exceed.VNE. Never Exceed Speed. Speed that should not be exceed anytime.VS. Stalling Speed. Minimum speed before stall.VX. Maximum Angle of Climb Speed.VY Maximum Rate of Climb Speed.

METEOROLOGICAL TERMINOLOGY

OAT. Outside Air Temperature

Standard Temperature.Temperature given by ISA at specific altitude.Pressure Altitude. Altitude given by ISA at specific pressure.

WEIGHT AND BALANCE TERMINOLOGY

CG. Center of Gravity.OEW. Operational Empty Weight.MTOW. Maximum Take Off Weight.MLW. Maximum Landing Weight.

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SECTION 2: LIMITATIONS

Introduction

On this section, the main limitations for the aircraft are given, according to general securityaspects from the FAA. As an electric powered aircraft, maximum speeds are never exceededon straight an level flight, and most of the times structural damage speeds or loads are notreached on climb because of stall limitations, but the operator of the UAV must take inaccount the restrictions during pull down maneuvers or hard turns.

Airspeed Limitations

Speed TAS m/s KTAS Remarks

VNENever Exceed

Speed38,6051 75,04

This is themaximum speed

given by theAircraft.

VA

ManeuveringSpeed

7 Kg

15,81 30,72

This speed isthe maximumallowed for themaximum turn

rate at sea level.

NOTE:Most of the FAA speed limitations are given for reciprocating engine aircrafts. This UAV, as asmaller airplane has some different speed limitations and in the case of the Never ExceedSpeed, this is given by the engine power and it must be taken also as a security mark forpull down maneuverings, where aerodynamic forces are critical because of gravity positiveacceleration. Also, this aircraft has no flaps or high-lift devices.

Power Plant Limitations

Engine Manufacturer.Model Motors S.R.O. Czech RepublicEngine Model Number.AXI 4120/18 Gold LineEngine Type.Electric Neodymium Magnets Motor. 6 mm Shaft Diameter. 515 RPM/V.Engine Rated Power.1000 Watts1,34 HPPropeller Manufacturer.APC PropellersPropeller Diameter.12-14 inches - 304-355 mmPropeller Type.Fixed PitchNumber of Blades.2Pitch.10 in254 mm

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Center of Gravity Limitations

UAV Category

Center of gravity rangeForward:10,04 cm3,95 inAfter: 11,035 cm4,34 inReference Datum: Measured from the leading edge of the wing, according to themaximum thickness and the 33% for R/C model general maximum limits.

NOTE:Forward Center of Gravity Limit is taken from the maximum thickness at meanaerodynamic chord for a Clark Y airfoil, used on this aircraft. After or Backward Center ofGravity Limit is taken at 33% from the leading edge of the airfoil, as usually used on R/C

aircrafts and mentioned by the manufacturer. Restrictions Based on Marti Molesky SJReports.

Flight Load Factor Limits for Turning Flights

AltitudeMaximum Turn

RateKTAS Load Factor

Sea level 126/s 30,73 3,68

10000 Ft 75,8/s 34,67 2,64

13000 Ft 48/s 37,51 1,91

Kind of Operation Limits

This UAV is mainly designed for recognition and recording during day operation, unless theinstallation of a night vision light camera. The service ceiling for the aircraft is about 15110ft over the sea level, but the quality of the camera is an important factor on operation atpatrolling or video-photography recording. As an UAV, the range is limited not only by thebattery charge, but its limited by the radio contact range, taking in account that large-rangeequipment are heavier and may compromise the performance of the aircraft.

Battery Limits

2 Batteries maximum allowed to avoid overweight on the aircraft.Kind of Battery: Li-PoIdeal Energy Capacity: 5000 mAhUnusable charge: about 1000 mAhNominal Voltage 22,2 V

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SECTION 3: PERFORMANCE

Introduction

This section includes the behavior of the aircraft on the principal operation stages, as takeoff, climb, cruising, gliding and landing. It also includes some conversion charts for KTASand KCAS. Some variations on the environmental conditions, mainly on temperature anddensity are taken in account and the corresponding charts are included.

Airspeed Calibration at 5000 ft

Speed5

m/s10

m/s15

m/s20

m/s25

m/s30

m/s35

m/s40

m/s45

m/s

KTAS 9,7 19,4 29,2 38,9 48,6 58,3 68 77,8 87,5

KCAS 9,02 18,04 27,06 36,09 45,11 54,13 63,15 72,18 81,2

0

10

20

30

40

50

60

70

80

90

100

0 20 40 60 80

KCAS

KTAS

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Airspeed Calibration at 10000 ft

Speed5

m/s10 m/s 15 m/s 20 m/s 25 m/s 30 m/s 35 m/s 40 m/s 45 m/s

KTAS 9,7 19,4 29,2 38,9 48,6 58,3 68 77,8 87,5

KCAS 8,35 16,70 25,06 33,42 41,79 50,17 58,56 66,96 75,37

Airspeed Calibration at 15000 ft

Speed5

m/s10 m/s 15 m/s 20 m/s 25 m/s 30 m/s 35 m/s 40 m/s 45 m/s

KTAS 9,7 19,4 29,2 38,9 48,6 58,3 68 77,8 87,5KCAS 7,70 15,42 23,13 30,86 38.59 46,33 54,09 61,86 69,65

0

10

20

30

40

50

60

70

80

90

100

0 10 20 30 40 50 60 70 80 90

KCAS

KTAS

0

10

20

30

40

50

60

70

80

90

0 10 20 30 40 50 60 70 80 90 100

KCAS

KTAS

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Temperature conversion Chart (Fahrenheit to Celsius)

Example:

Most of the charts below are represented in Celsius scale. If your instrument indicates 65F, you canprobably use the 20C OAT data, according to the relation on this chart.

-15,00

5,00

25,00

45,00

65,00

85,00

105,00

-25 -15 -5 5 15 25 35 45 55

Farenhe

it

Celsius

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Density Altitude Chart (Ft)

Example:

For 30C OAT and when the instrument is on 5000 ft of Pressure altitude, the correct density altitudeto take in account is approximately 7800 Ft. It means that the density altitude to take in account ishigher than the pressure altitude indicated.

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

-20 -10 0 10 20 30 40

DensityAltitude

ft

Temperature C

0

1000

2000

3000

4000

5000

6000

7000

8000

9000

10000

11000

12000

13000

14000

15000

ISA

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Stall Speed with Maximum Take Off Weight

ANGLE OF BANK

0 30 45 60

TAS m/s KTAS TAS m/s KTAS TAS m/s KTAS TAS m/s KTAS

At sea level 10,44 20,30 11,22 21,81 12,42 24,14 14,77 28,71

At 5000 ft 11,25 21,87 12,09 23,51 13,38 26,017 15,91 30,94

Example:

At 4500 Ft pressure Altitude, you must be careful at rolling at least at 21,5 Knots with only 30 Angle of Bank.The faster you go, the leaner you can turn without reaching stall conditions.

Take Off Parameters

0 Knots Headwind

Weights

Take off speeds

(Knots) Altitude

(Ft)

0C 15C 30C

Lift Off At 50 ftGroundroll (m)

Total(m)

Groundroll (m)

Total(m)

Groundroll (m)

Total(m)

7 Kg

56,47 29,970 117,68 177,75 129,9 191,78 141,027 204,5

58,54 31,102000 134,25 196,67 145,66 209,8 156 222

60,76 32,264000 149,83 214,73 160,69 227,4 170,63 239,2

63,07 33,496000 164,94 232,45 175,4 244,84 185,2 256,5

65,52 34,798000 179,75 250 190 262,27 199,7 273,95

68,09 36,1610000 194,54 267,68 204,77 279,97 214,49 291,7

10 Knots Headwind

Weights

Take off speeds(Knots) Altitude

(Ft)

0C 15C 30C

Lift Off At 50 ftGroundroll (m)

Total(m)

Groundroll (m)

Total(m)

Groundroll (m)

Total(m)

7 Kg

56,47 29,970 117,35 177,4 129,6 191,45 140,6 204,1

58,54 31,102000 133,92 196,34 145,33 209,54 155,74 221,6

60,76 32,264000 149,54 214,44 160,36 227,12 170,38 238,9

63,07 33,496000 164,611 232,12 175,08 144,51 184,8 256,17

65,52 34,798000 179,42 249,67 189,708 261,95 199,41 273,59

68,09 36,1610000 194,21 267,35 204,44 279,64 214,16 291,3

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15 Knots Headwind

Weights

Take off speeds

(Knots) Altitude

(Ft)

0C 15C 30C

Lift Off At 50 ft Groundroll (m)

Total(m)

Groundroll (m)

Total(m)

Groundroll (m)

Total(m)

7 Kg

56,47 29,970 116,41 176,48 128,72 190,51 139,75 203,23

58,54 31,102000 132,98 195,411 144,39 208,6 154,8 220,76

60,76 32,264000 148,6 213,5 159,49 226,18 169,44 238,01

63,07 33,496000 163,67 231,18 174,14 243,57 189,94 255,24

65,52 34,798000 178,48 248,74 188,77 261 198,48 272,65

68,09 36,16

10000 193,28 266,46 203,5 278,7 213,22 290,43

Example:Departure runway pressure altitude: 4000 Ft.OAT 17CWind: 15 Knots HeadwindGross Weight: 7 KgTake Off Distance: Approximately 161 m for ground roll and 228 m for V2. Take in account that with theincrease on the temperature and altitude, you will probably need a larger runway.

NOTE:Ground Roll distances are calculated according to stall speed for a lift coefficient of 0,2,according to the angle of attack of the wing with the aircraft in land. Distances are

calculated on Dry concrete. Ground roll on grass may be greater due the effect of the frictionof grass on small UAV Tires. Total distance includes an obstacle height of 15 m or 50 ft andan average lift coefficient of 0,775, according to the angle of attack variation during rotation.

Rate of Climb

WEIGHT ALTITUDECLIMB SPEED

(Knots)

RATE OF CLIMB (FPM)

ISA-20 ISA ISA+20 ISA+40

7 Kg

0 23,35815054 1723,058916 1701,865137 1680,671358 1659,47758

3000 24,41773054 1415,186346 1391,538377 1367,890408 1344,24244

6000 25,54949217 1104,341604 1077,89364 1051,445676 1024,997712

9000 26,7600685 790,1095195 760,4579518 730,8063842 701,1548165

12000 28,05686703 472,0061676 438,6783336 405,3504997 372,0226658

15000 29,44818016 149,4656146 111,906033 74,34645143 36,78686985

Example:At 6000 Ft, for ISA+20, the maximum rate of climb that you can get is about 1051,5 Ft. If you want to climb to7000 Ft it will probably take almost 1 minute (57 seconds). For big increases, this calculation must be done byintervals, due the R/C variation with altitude.

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NOTE:Power and Thrust given by the engine-propeller joint may be affected by height. Thisvariation is taken form experimental data, where the service ceiling is about 15110 Ft overthe sea level. This variation on power is generated by the density decrease with altitude,where the joint propels less air per revolution.

Time and Distance on Climb

Weight Altitude (Ft) OAT CClimb Speed

(Knots)Rate of Climb

(FPM)Time (min) Distance (NM)

7 Kg

0 40 24,34 1675,53 0 0

1000 35 24,59 1574,77 2 0,81

2000 30 24,84 1473,88 4 1,65

3000 25 25,09 1372,86 6 2,50

4000 20 25,34 1271,70 8 3,37

5000 15 25,60 1170,41 10 4,26

6000 10 25,85 1068,98 12 5,17

7000 5 26,11 967,42 14 6,09

8000 0 26,38 865,72 16 7,03

9000 -5 26,64 763,89 18 7,99

10000 -10 26,91 661,93 20 8,97

11000 -15 27,17 559,84 22 9,96

12000 -20 27,44 457,63 24 10,97

13000 -25 27,71 355,29 26 12,01

14000 -30 27,98 252,84 28 13,06

15000 -35 28,26 150,27 30 14,13

Example:Departure runway pressure altitude: 7000 Ft.OAT 7CGross Weight: 7 Kg

Climb Speed: About 26,11 KnotsRate of climb: About 970 FPMTime to climb: About 14 minutesDistance during climb: 6 NMIncrease on the altitude generates slower rate of climb. This means more time to get a higher altitude. Above15000 Ft, climbing is not recommended, due the restrictions of the engine and stall speeds.

Maximum Climb Angle

MAXIMUM CLIMB ANGLE

WEIGHT Altitude Ft

CLIMB SPEED FOR

MAX ANGLE

(Knots)

ISA-20 ISA ISA+20 ISA+40

7 Kg

6000 18,27 Not available 72,81 62,45 55,76

6750 25,36 64,37 56,20 50,35 45,78

7750 29,61 47,55 42,69 38,78 35,54

8750 32,20 36,03 32,55 29,65 27,19

9750 34,03 26,79 24,16 21,93 20,01

10750 35,41 18,85 16,81 15,07 13,57

11750 36,49 11,66 10,07 8,72 7,54

12750 37,33 4,78 3,56 2,51 1,60

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Example:Flying Pressure Altitude: 11500 Ft.Conditions ISA+20Gross Weight: 7 KgClimb Speed: About 36,5 KnotsMaximum climb angle: About 8,7

Angles above Maximum climb angle cant be reached, and if they are, it will generate stall or failure at controls.

NOTE:For other altitudes above 12750 ft or less than 6000 ft, maximum climb angle cant bereached due the effect of stall. Although, the maximum rate of climb is not necessarilyrelated with the maximum climb angle, and for these altitudes, maximum rate of climb isgenerally used.

Cruise Parameters

PRESSURE

ALTITUDE

(Ft)

OAT -20C OAT 0C OAT 20C OAT 40C

Power KTAS Power KTAS Power KTAS Power KTAS

3000

55%57,05

55%58,41

55%59,73

55%60,95

65%60,64

65%62,14

65%63,54

65%64,90

75%63,87

75%65,44

75%66,96

75%68,38

5000

55%55,78

55%57,14

55%58,50

55%59,67

65%59,48

65%60,84

65%62,20

65%63,56

75%62,59

75%64,34

75%65,70

75%67,06

10000

55%50,92

55%51,90

55%53,06

55%54,03

65%54,81

65%55,78

65%57,14

65%58,12

75%57,92

75%59,09

75%60,45

75%61,81

13000

55%44,90

55%45,87

55%46,26

55%46,84

65%49,17

65%50,15

65%50,92

65%51,90

75%52,67

75%53,84

75%54,81

75%55,78

Example:Cruise pressure altitude: 9000 Ft.OAT 3CGross Weight: 7 KgPower Output: 75%Speed at this power output: 57 Knots.Higher speeds cant be reachedat this altitude with 75% Power. To get higher speed with this Power percentage,take a lower cruise altitude. This will make the propeller joint more efficient, but it would also generate more

drag, reducing the endurance.

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Range

For OAT: -20 C For OAT: 0 C

For OAT: 20 C For OAT: 40 C

NOTE: Power Variation lines are ordered from left to right, where the left line represents75% power, centerline represents 65% power and right line represents 55% power.

2000

4000

6000

8000

10000

12000

14000

6 11 16

Altitudeft

Range NM

2000

4000

6000

8000

10000

12000

14000

6 11 16

Altitudeft

Range NM

2000

4000

6000

8000

10000

12000

14000

6 11 16

Altitudeft

Range NM

2000

4000

6000

8000

10000

12000

14000

6 11 16

Altitudeft

Range NM

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Endurance

NOTE: Endurance has no considerable variation with altitude due the kind of engine usedon this UAV. Generally, electric motors are not affected by environmental temperaturevariations, and, even though the power given by the engine-propeller joint could be reducedby density decrease, the energy consumed by the engine is the same. (Simply this energy isnot totally used and it is wasted).

Example for Range and Endurance:Departure Runway pressure altitude: 4000 Ft.OAT 10CGross Weight: 7 KgPower Output: 75%Speed at this power output: 57 Knots.Range: About 15 NM Until Batteries discharge.

Endurance: About 14 Minutes.To get further ranges, use 55% Power. It will increase the endurance and the Range, but you will get slowerspeed.

Gliding distance

1000

3000

5000

7000

9000

11000

13000

10 12 14 16 18 20 22

AltitudeFt

Endurance (Minutes)

55% Potencia

65% Potencia

75% Potencia

0

2000

4000

6000

8000

10000

12000

14000

16000

0 20000 40000 60000 80000 100000 120000 140000 160000 180000

Altitu

de(Ft)

Distance (Ft)

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NOTE:The gliding distance are assumed with a descent angle of 5,04 nose down, or -5,04. Thisgliding angle is based on the maximum aerodynamic efficiency, with 11,32 Lift Units perevery Drag Unit. These distances should not be affected by temperature or density

variations, because its only affected by drag coefficients and geometrical relations on theaircraft.

Example for Engine Loss:Engine Loss Pressure altitude: 12000 FtDistance: About 22 NMAngle of Descent: 5,04 Nose DownSpeed: 36,9 Knots. According to the Maximum Efficiency Speed (See the next Chart)If you lose the engine at lower speed than Maximum efficiency speed, you should dive softly the Aircraft untilreach the Maximum efficiency speed. When this speed is reached stop diving and put 5,04 Nose Down. Thenrecalculate your gliding distance at the new altitude. This maneuver is made to avoid reaching stall speed with

an engine loss.

0

2000

4000

6000

8000

10000

12000

14000

16000

0 5 10 15 20 25 30

Altitude(Ft)

Distance (NM)

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Gliding speeds and distances

Altura

(ft)

Altura

(m)

V(L/D) max

KTAS

Sink Rate

(m/s)

Gliding

Distance (ft)

Gliding

Distance (m)

Gliding

Distance

(NM)

1000304,8 31,19 -757,62

11322,77 3439,851,86

2000609,6 31,59 -770,25

22645,54 6879,713,72

3000914,4 32,15 -780,14

33968,31 10319,575,58

40001219,2 32,59 -793,95

45291,08 13759,437,44

5000 1524 33,05 -804,80 56613,85 17199,28 9,30

60001828,8 33,69 -816,11

67936,62 20639,1411,16

70002133,6 34,19 -831,96

79259,39 24079,0013,02

80002438,4 34,72 -844,47

90582,16 27518,8614,88

90002743,2 35,28 -857,57

101904,93 30958,7116,74

100003048 35,67 -871,29

113227,70 34398,518,60

11000

3352,8 36,27 -880,81

124550,47 37838,43

20,46

120003657,6 36,90 -895,70

135873,24 41278,2922,32

130003962,4 37,57 -911,37

147196,01 44718,1424,18

140004267,2 38,04 -927,89

158518,78 48158,0026,04

150004572 38,77 -939,42

169841,55 51597,8627,90

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Landing Parameters

0 Knots Headwind

Weights

Landing speeds(Knots) Altitude

(Ft)

0C 15C 30C

ApproachTouch

Down

Ground

roll (m)

Total

(m)

Ground

roll (m)

Total

(m)

Ground

roll (m)

Total

(m)

7 Kg

33,90 29,99 0 184,77 474,63 194,87 484,92 205 495,25

35,160 31,10 2000 198,66 488,78 209,56 499,9 220,51 511

36,46 32,26 4000 213,87 504,3 225,68 516,55 237,52 528,419

37,86 33,49 6000 230,59 521,34 243,38 534,38 256,23 547,48

39,32 34,79 8000 248,97 540,09 262,87 554,25 276,82 568,477

40,88 36,15 10000 269,25 560,75 284,36 576,15 299,54 591,63

10 Knots Headwind

Weights

Landing speeds

(Knots) Altitude(Ft)

0C 15C 30C

ApproachTouch

Down

Ground

roll (m)

Total

(m)

Ground

roll (m)

Total

(m)

Ground

roll (m)

Total

(m)

7 Kg

33,901 29,99 0 154,16 444,02 164,18 454,23 174,23 464,48

35,160 31,10 2000 167,98 458,065 178,76 469,1 189,63 480,19

36,46 32,26 4000 183,04 474,47 194,77 485,43 206,5 497,44

37,86 33,49 6000 199,65 490,41 212,37 503,39 225,16 516,41

39,32 34,79 8000 217,94 509,059 231,77 523,15 245,67 537,32

40,88 36,15 10000 238,12 529,63 253,17 533,97 268,3 560,39

7/24/2019 FINAL POH

24/24

15 Knots Headwind

Weights

Landing speeds

(Knots) Altitude

(Ft)

0C 15C 30C

ApproachTouchDown

Groundroll (m)

Total(m)

Groundroll (m)

Total(m)

Groundroll (m)

Total(m)

7 Kg

33,90 29,99 0 122,48 412,33 132,17 422,22 141,92 432,17

35,160 31,10 2000 135,81 425,94 146,67 436,67 156,91 447,47

36,46 32,26 4000 150,49 440,92 161,91 452,57 173,42 464,31

37,86 33,49 6000 166,68 457,43 179,11 470,11 191,63 482,88

39,32 34,79 8000 184,67 475,67 198,11 489,49 211,75 503,4

40,88 36,15 10000 204,34 495,85 219,12 510,92 234,011 526,09

Example:Landing runway pressure altitude: 4000 Ft.OAT 17CWind: 15 Knots HeadwindGross Weight: 7 KgLanding Distance: Approximately 455 m of total runway, taking in account 163 m for ground roll. Take inaccount that with the increase on the temperature and altitude, you will probably need a larger runway.

NOTE:Ground Roll distances are calculated according to stall speed for a lift coefficient of 0,2,according to the angle of attack of the wing with the aircraft in land. Distances arecalculated on Dry concrete. Ground roll on grass may be greater due the effect of the friction

of grass on small UAV Tires. Total distance includes an obstacle height of 15 m or 50 ft andan average lift coefficient of 0,775, according to the angle of attack variation duringapproach.