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Lee-side flow phenomena on space shuttle configurations at hypersonic speeds. Part 2: Studies of lee-surface heating at hypersonic Mach numbersLee surface heating data, obtained at relatively low unit Reynolds numbers at Mach 6 and 19, are discussed with emphasis on the peak heating behavior. Surface pressures measured along the lee meridian of the delta-wing orbiter are presented and analyzed in conjunction with the heating. The effects of nose bluntness and lee surface geometry on the heating are discussed and general guidelines are presented for modifying the lee surface geometry of the shuttle to reduce vortex-induced heating. The application of the wind tunnel results to realistic shuttle flight conditions is discussed.
Document ID
19720013213
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hefner, J. N.
(NASA Langley Research Center Hampton, VA, United States)
Whitehead, A. H., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 6, 2013
Publication Date
February 1, 1972
Publication Information
Publication: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2
Subject Category
Thermodynamics And Combustion
Accession Number
72N20863
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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