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Experimental and Numerical Optimization of a High-Lift System to Improve Low-Speed Performance, Stability, and Control of an Arrow-Wing Supersonic TransportAn investigation was performed to evaluate leading-and trailing-edge flap deflections for optimal aerodynamic performance of a High-Speed Civil Transport concept during takeoff and approach-to-landing conditions. The configuration used for this study was designed by the Douglas Aircraft Company during the 1970's. A 0.1-scale model of this configuration was tested in the Langley 30- by 60-Foot Tunnel with both the original leading-edge flap system and a new leading-edge flap system, which was designed with modem computational flow analysis and optimization tools. Leading-and trailing-edge flap deflections were generated for the original and modified leading-edge flap systems with the computational flow analysis and optimization tools. Although wind tunnel data indicated improvements in aerodynamic performance for the analytically derived flap deflections for both leading-edge flap systems, perturbations of the analytically derived leading-edge flap deflections yielded significant additional improvements in aerodynamic performance. In addition to the aerodynamic performance optimization testing, stability and control data were also obtained. An evaluation of the crosswind landing capability of the aircraft configuration revealed that insufficient lateral control existed as a result of high levels of lateral stability. Deflection of the leading-and trailing-edge flaps improved the crosswind landing capability of the vehicle considerably; however, additional improvements are required.
Document ID
20000021552
Acquisition Source
Headquarters
Document Type
Technical Publication (TP)
Authors
Hahne, David E. (NASA Langley Research Center Hampton, VA United States)
Glaab, Louis J. (Lockheed Engineering and Sciences Co. Hampton, VA United States)
Date Acquired
September 7, 2013
Publication Date
December 1, 1999
Subject Category
Aerodynamics
Report/Patent Number
NASA/TP-1999-209539
NAS 1.60-209539
L-17537
Funding Number(s)
PROJECT: RTOP 537-03-22-08
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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