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Supersonic Aerodynamic Design Improvements of an Arrow-Wing HSCT Configuration Using Nonlinear Point Design MethodsThis paper is a discussion of the supersonic nonlinear point design optimization efforts at McDonnell Douglas Aerospace under the High-Speed Research (HSR) program. The baseline for these optimization efforts has been the M2.4-7A configuration which represents an arrow-wing technology for the High-Speed Civil Transport (HSCT). Optimization work on this configuration began in early 1994 and continued into 1996. Initial work focused on optimization of the wing camber and twist on a wing/body configuration and reductions of 3.5 drag counts (Euler) were realized. The next phase of the optimization effort included fuselage camber along with the wing and a drag reduction of 5.0 counts was achieved. Including the effects of the nacelles and diverters into the optimization problem became the next focus where a reduction of 6.6 counts (Euler W/B/N/D) was eventually realized. The final two phases of the effort included a large set of constraints designed to make the final optimized configuration more realistic and they were successful albeit with a loss of performance.
Document ID
20000044868
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Unger, Eric R.
(McDonnell-Douglas Aerospace Long Beach, CA United States)
Hager, James O.
(McDonnell-Douglas Aerospace Long Beach, CA United States)
Agrawal, Shreekant
(McDonnell-Douglas Aerospace Long Beach, CA United States)
Date Acquired
August 19, 2013
Publication Date
December 1, 1999
Publication Information
Publication: First NASA/Industry High-Speed Research Configuration Aerodynamics Workshop
Issue: Part 3
Subject Category
Aircraft Design, Testing And Performance
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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