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Supersonic Channel Concept for Enhancement of Lift/Drag RatioThe concept studied during the summer NASA/ASEE Fellowship provides a means of lowering drag and a means for directional control of supersonic and hypersonic vehicles. Low drag and efficient directional control are essential for the success of aircraft, atmospheric entry vehicles, missiles, and other vehicles in supersonic and hypersonic flight. Drag reduction can result in increased vehicle range, increased speed, improved fuel efficiency, increased lift/drag ratio, and increased climb rate. For high supersonic and hypersonic vehicles heat transfer considerations dictate the design of the nose and leading edge. The heat transfer to such vehicles is most severe at stagnation points which occur on the leading edges and nose of the vehicle. Theoretical formulations, experimental data, and semi-empirical formulas all agree in the fact that stagnation point heat transfer is inversely proportional to the square root of the nose or leading edge radius. Thus, the noses and leading edges of supersonic and hypersonic vehicles are typically blunted so that the heat transfer and structural loads will be manageable. However, much of the wave drag experienced by these vehicles is due to nose blunting.
Document ID
19970010174
Document Type
Other
Authors
Ruffin, Stephen M. (Georgia Inst. of Tech. Atlanta, GA United States)
Date Acquired
August 17, 2013
Publication Date
October 1, 1996
Subject Category
Aerodynamics
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19970010146Analytic Primary1996 NASA-ASEE-Stanford Summer Faculty Fellowship Program
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