Stowability Constraint Within a Two-Dimensional Aerodynamic Optimization Method

Kolla, Maureen L.; Yokota, Jeffrey W.; Lassaline, J. V.; Fejtek, Ian

doi:10.2514/1.34863

Cited by 6 publications

(1 citation statement)

References 9 publications

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“…Multidisciplinary aspects related to high-lift system are presented by v. Dam et al, 4 Takenaka and Nakahashi, 5 and Kolla et al. 6 These publications deal with the aerodynamic optimization of high-lift systems under consideration of the flap mechanism. In a previous publication 7 the author focuses on the aeromechanical setting optimization of the flap.…”

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Investigation on continuously deflectable High-Lift Devices for a 3D High-Lift Configuration

Franke

2015

33rd AIAA Applied Aerodynamics Conference

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This work deals with the investigation of continuously deflectable high-lift devices. The aim of this work is to derive optimal high-lift settings for off-design conditions and to evaluate the benefits of this technology. Off-design is related in this context to airport, aircraft and atmospheric specific conditions. Within the work a fully automatized process chain (high-fidelity methods are used) is implemented to generate an aerodynamic database for various high-lift settings. This data base is used by a preliminary design tool to simulate the overall aircraft for take-off, approach and landing at off-design. The resulting data are fed in a response surface model (RSM) to obtain the overall behavior for the slat/flap deflection angle domain. The interpolated values are used to derive optimal high-lift settings. The results show consistent behavior. It is found that for take-off valuable benefits can be achieved. For landing the results indicate that a further flap deflection than the standard landing setting is beneficial. NomenclatureAoA Aircraft angle of attack,MAC Mean aerodynamic chord length, [m] M Mach-number, [-] Re Reynolds-number, [-] S Reference area, [m 2 ] t Temperature, [ • C] T /W Thrust to weight ratio, [N/kg] T rev Reverse thrust, [N] v Velocity, [m/s] v s1g 1-g stall speed, [m/s] W Weight, [kg] W/S Wing-loading, [kg/m 2 ] AEO All engines operative BFL Balanced field length CAD Computer aided design CFD Computational fluid dynamics FAA Federal aviation administration ISA International standard atmosphere LFL Landing field length LW Landing weight MLW Maximum landing weight MTOW Maximum take-off weight OEI One engine inoperative OEW Operating empty weight RSM Response surface model TOFL Take-off field length TOW Take-off weight Symbols δ Deflection angle, [ • ] γ Flight path angle, [ • ] µ rGround roll friction coefficient, [-]

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Investigation on continuously deflectable High-Lift Devices for a 3D High-Lift Configuration

Franke

2015

33rd AIAA Applied Aerodynamics Conference

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Aerodynamic Optimization of a High-Lift System with Kinematic Constraints

Franke

2013

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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The design of the high-lift system is crucial for the economical success of a commercial airplane. The aim of this work is to find an optimized high-lift system with improved aerodynamic performance and kinematic properties. The analysis presented in this work covers the simulation of the aerodynamics and the kinematics, which are embedded in an optimization framework. The optimization revealed a configuration that fulfills the kinematic constraints and an improvement in the aerodynamic performance. It can be stated that the consideration of additional kinematic constraints for an aerodynamic setting optimization leads to a more realistic design.

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