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Design Innovation

Multidisciplinary Optimization of Supersonic Aircraft Including Low-Boom Considerations

[+] Author and Article Information
Joël Brezillon

 German Aerospace Centre (DLR), Institute of Aerodynamics and Flow Technology, Lilienthalplatz 7, D-38108 Braunschweig, GermanyJoel.Brezillon@dlr.de

Gerald Carrier

The French Aerospace Lab (ONERA), Applied Aerodynamics Department, 8 rue des Vertugadins, F-92190 Meudon, FranceGerald.Carrier@onera.fr

Martin Laban

National Aerospace Laboratory (NLR), Aerospace Vehicles Division, Anthony Fokkerweg 2, 1059 CM Amsterdam, The NetherlandsLaban@nlr.nl

J. Mech. Des 133(10), 105001 (Oct 25, 2011) (9 pages) doi:10.1115/1.4004972 History: Received January 14, 2010; Revised August 15, 2011; Accepted August 31, 2011; Published October 25, 2011; Online October 25, 2011

This paper presents a multidisciplinary optimization framework developed by the authors and applied to small-size supersonic aircraft. The multidisciplinary analysis suite is based on the combination of low (empirical) and high-fidelity computational fluid dynamics (CFD) and computational structure mechanics (CSM) tools for predicting the overall aircraft performance and the sonic boom overpressure at supersonic flight, which represents the most challenging environmental constraint for supersonic aircraft. The analysis suite is coupled with a multi-objective optimization strategy for quantifying the trade-off between the maximum take-off weight, mission range, and the sonic boom overpressure. The optimization framework is applied to a small-size supersonic business-jet cruising at Mach number M = 1.8 and featuring a double delta wing. The trade-offs between disciplines are well captured and an optimized configuration achieving the target mission range with a lower maximum take-off weight, and a moderate sonic boom signature is obtained through changes in wing dihedral and sweep. A more drastic reduction of the sonic boom signature is also obtained but at the cost of a significant reduction of the aircraft performance.

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Copyright © 2011 by American Society of Mechanical Engineers
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Figures

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Figure 1

Design structure matrix representation of the mixed-level fidelity suite

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Figure 2

Design variables of a generic wing geometry

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Figure 3

Wing internal structural elements

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Figure 4

Pressure field computed on the low-boom shape configuration (M =  1.8)

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Figure 5

Three-layer sonic boom prediction methodology

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Figure 6

Sonic boom signature at the ground for the low-boom shape configuration

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Figure 7

Shape of the low-boom concept

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Figure 8

Overview of the database for all feasible evaluated configurations black squares is the configurations belonging to the Pareto front between range and MTOW

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Figure 9

Pressure distribution for the baseline and the Pareto optimal configurations (M = 1.8)

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Figure 10

View of the wing dihedral for the baseline and the Pareto optimal configurations

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Figure 11

Sonic boom signature for the baseline and the Pareto optimal configurations

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Figure 12

Overpressure and underpressure versus mission range for all feasible evaluated configurations black squares represent the configurations belonging to the Pareto front between range and MTOW

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Figure 13

Sonic boom signature for the baseline, Pareto optimal, and lowest overpressure configuration

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Figure 14

View of the wing dihedral for the baseline, Pareto optimal, and lowest overpressure configuration

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