Design Aspects of Passenger Box Wing Aircraft · Design Aspects of Passenger Box Wing Aircraft ......

AIRCRAFT DESIGN AND SYSTEMS GROUP (AERO)

Design Aspects of Passenger Box Wing Aircraft

3rd Symposium on Collaboration in Aircraft Design

Linköping, Sweden

19 to 20 September 2013

Dieter Scholz Hamburg University of Applied Sciences

Ricardo Caja Calleja Hamburg University of Applied Sciences

Linköping, Sweden, 19. - 20.09.2013

Dieter Scholz

Box Wing Aircraft18.09.2013, Slide 2

Aircraft Design and Systems Group (AERO)

Abstract

Future passenger aircraft strive for less fuel consumption, but their design is driven

by the requirement at airports of a maximum of e.g. 36 m wing span for short/medium

range aircraft. A box wing aircraft staying within the 36 m limit could achieve a drastic

reduction in induced drag and hence fuel consumption. Indeed, box wing aircraft have

been considered since decades, but so far very little has been done proposing a type

that can be certified and is suitable to be used by every day airline operation. This

investigation selects the best configuration from a modified morphological analysis,

looks at performance, aerodynamic and longitudinal static stability, cabin/fuselage

layout, family concepts and ground handling. A model of such proposed aircraft was

built with rapid prototyping. With all this, the presented material and facts should

serve as a baseline for a realistic discussion about the chances of a box wing

configuration to be the next generation short/medium range aircraft.

Dieter Scholz

Content

Requirements at Airports

Morphological Analysis

Performance

Aerodynamics

Longitudinal Static Stability

Cabin and Fuselage Layout

Aircraft Family

Ground Handling

Rapid Prototyping

Dieter Scholz

Requirements at Airports …

… are Driving Todays Aircraft Design!

Dieter Scholz

• Hand Sketches

• Creative Methods

• Brainstorming• Gallery Method

Dieter Scholz

Example of possible vertical tails

All possible variations together (from Bachelor thesis) would lead to 31104000 combinations

Dieter Scholz

• Morphological Analysis

Number of Combinations: 3 .

3 . 1 . 3 = 162

Successive combination (in „best“ order) followed by immediate down selection => 18

after down selection

• Modified Morphological Analysis

Dieter Scholz

18 Candidates from Modified Morphological Analysis …

Dieter Scholz

… 18 Candidates from Modified Morphological Analysis

Dieter Scholz

German: „Nutzwertanalyse“ (ZANGEMEISTER): Weighted Sum of Evaluation Points

• Configuration• Force Fighting• Family Concept

• Drag• Zero Lift Drag• Induced Drag

• Weight• Empty Weight

• Flight Mechanics• Longitudinal Static Stability and CG Range

• Operation• Ground Handling

• Development• Time and Cost• Risk

Morphological Analysis – Evaluation

Dieter Scholz

Morphological Analysis – Results

Best unconvential configuration

Dieter Scholz

General Box Wing Performance

If the ideal case (infinite

) where is considered:

Box Wing flies at reference Aircraft Altitude

Reference Aircraft flies at Box Wing Altitude

„Fair“ comparison:

Dieter Scholz

Measurements of induced drag of different box wings in thewind tunnel of HAW Hamburg

The reference wing

Box Wing Aerodynamics

Dieter Scholz

Box Wing Aerodynamics – Induced Drag

0,0 0,1 0,2 0,3 0,4 0,5 0,6 0,7 0,8 0,9 1,0

(c) k Prandtl

(d) k Rizzo

(a) k Prandtl (Biplane)

(b) k Prandtl (Biplane 2)

k from iDrag results fit to

"box wing equation" with

parameters from (f)k from iDrag results fit to

"winglet equation"

k DeYoung

k iDrag results

k from wind tunnel data

boxi==

Dieter Scholz

boxi==

⋅+==

Box Wing Aerodynamics – Induced Drag

Dieter Scholz

Box Wing Aerodynamics – Induced Drag and Lift Share

From Lockheed Report

Dieter Scholz

Sensitivity of induced drag to non-optimum lift distributions (Tornado) – Stagger = 0

Box Wing Aerodynamics – Lockheed versus Tornado – No Stagger

Dieter Scholz

Sensitivity of induced drag to non-optimum

lift distributions (Tornado) – Stagger = -0.5b

Box Wing Aerodynamics – Lockheed versus Tornado – Negative Stagger

Dieter Scholz

h: C/G position as multiple of the length of MAC1,

measured from the

leading edge of MAC1

Control LimitCL,2 needs to be low. Thus for a given CL

CL,1 needs to be increased

needs to be as high as possible

Stability Limit

Trim Condition

CL,2 needs to be lower than CL,1

L⋅+<

Box Wing Longitudinal Static Stability

Dieter Scholz

C/G Envelope Diagrams

CL,1 = CL,2 CL,1/CL,2 = 1,74

A further increase of the C/G envelope

requires a higher CL,1/CL,2!

unstable! stable!

Dieter Scholz

Design Measures for Stability

Dieter Scholz

Cabin and Fuselage Layout

Dieter Scholz

Aircraft Family

Dieter Scholz

Aircraft Family

Dieter Scholz

Summary of Ground handling equipment on V100 and the ramp layout

Ground Handling

Dieter Scholz

Summary of Ground handling equipment on S200 and the ramp layout

Ground Handling

Dieter Scholz

Rapid Prototyping

Dieter Scholz

Rapid Prototyping

Dieter Scholz

Rapid Prototyping

Dieter Scholz

http://Airport2030.ProfScholz.de

Design Aspects of Passenger Box Wing Aircraft · Design Aspects of Passenger Box Wing Aircraft ......

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