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Heat transfer tests of the McDonnell-Douglas delta wing orbiter mated with -17A booster at Mach number 8A wind tunnel test program to determine aerodynamic heat transfer distributions on the McDonnell-Douglas configurations is reported. The tests were conducted at the Arnold Engineering Development Center (AEDC) in Tunnel B of the von Karman Gas Dynamics Facility (VKF). Heat-transfer rates were determined by the phase-change paint technique on 0.011-scale Stycast models using Tempilaq as the surface temperature indicator. The nominal test conditions were; Mach 8, freestream unit Reynolds numbers of 0.8 x one million, 2.5 x one million, and 3.7 x one million, and angles of attack of -5 deg, 0 deg, +5deg. Model details, test conditions, phase-change paint photographs and reduced heat-transfer coefficients are presented.
Document ID
19720021224
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Matthews, R. K. (Chrysler Corp. New Orleans, LA, United States)
Martindale, W. R. (Chrysler Corp. New Orleans, LA, United States)
Warmbrod, J. D. (Chrysler Corp. New Orleans, LA, United States)
Date Acquired
August 6, 2013
Publication Date
May 1, 1972
Subject Category
Space Vehicles
Report/Patent Number
DMS-DR-1262-VOL-1
NASA-SER-H-1011
NASA-CR-120067
Accession Number
72N28874
Funding Number(s)
CONTRACT_GRANT: NAS8-4016
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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