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Aerothermodynamic measurements on a proposed assured crew return vehicle (ACRV) lifting-body configuration at Mach 6 and 10 in airA 0.02-scale model of a lifting-body concept for possible application to the Assured Crew Return Vehicle from Space Station Freedom was tested at Mach 6 and 10 in air. Thermal mappings and surface streamline patterns were obtained at angles of attack ranging from 0 to 30 deg and unit Reynolds numbers Re from 2 to 8 x 10 to the 6th/ft. Areas that experienced the highest heating were near the model nose and tip-fin leading edges. The effect of Re on windward centerline heating coefficients was negligible, whereas increases in angles of attack produced increases in heating. At Mach 6 and the highest unit Re, turbulent heat at the windward centerline was three to four times the laminar level. Leeward crossflow separation and vortex reattachment along the centerline are evident across the Re and angle-of-attack ranges tested, indicative of a complex flowfield.
Document ID
19900051384
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Horvath, Thomas J.
(NASA Langley Research Center Hampton, VA, United States)
Rhode, Matthew N.
(NASA Langley Research Center Hampton, VA, United States)
Buck, Gregory M.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
June 1, 1990
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 90-1744
Accession Number
90A38439
Distribution Limits
Public
Copyright
Other

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