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Supersonic airplane design optimization method for aerodynamic performance and low sonic boomThis paper presents a new methodology for the optimization of supersonic airplane designs to meet the dual design objectives of low sonic boom and high aerodynamic performance. Two sets of design parameters are used on an existing High Speed Civil Transport (HSCT) configuration to maximize the aerodynamic performance and minimize the sonic boom under the flight track. One set of the parameters perturbs the camber line of the wing sections to maximize the lift-over-drag ratio (L/D). A preliminary optimization run yielded a 3.75 percent improvement in L/D over a baseline low-boom configuration. The other set of parameters modifies the fuselage area to achieve a target F-function. Starting from an initial configuration with strong bow, wing, and tail shocks, a modified design with a flat-top signature is obtained. The methods presented can easily incorporate other design variables and objective functions. Extensions to the present capability in progress are described.
Document ID
19920076743
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cheung, Samson H.
(MCAT Inst. Moffett Field, CA., United States)
Edwards, Thomas A.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 15, 2013
Publication Date
October 1, 1992
Publication Information
Publication: NASA. Langley Research Center, High-Speed Research: Sonic Boom, Volume 2
Subject Category
Aircraft Design, Testing And Performance
Accession Number
92X10697
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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