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Results of aeroheating DFI and ET design-data test on a 0.0175-scale model 60-OTS conducted in the Von Karman Gas Dynamics Facility (VKF) 40" supersonic and the 50" hypersonic wind tunnels A and CThe 0.0175-scale thin-skin thermocouple Model 60-OTS was tested in the von Karman Gas Facility 40-inch continuous flow supersonic tunnel A and the VKF Tunnel C. Testing was conducted at Mach numbers 2.25 to 4.0, and Reynolds numbers from 0.4 x 10 to the 6th power/ft to 6.6 x 10 to the 6th power/ft. Angle of attack range was from -5.0 to +5.0 degrees, and angle of sideslip range was from -6 to +6 degrees. The primary objective of this test was to provide a valid base for the external tank (ET) and solid rocket booster (SRB) heating prediction methodology for ascent flight by taking heating data at Development Flight Instrumentation (DFI) locations for flight conditions simulating STS-1 through -4. A second objective was to obtain additional aeroheating data to support potential reduction of the thermal protection system (TPS) on the ET. The third phase of the test was funded and conducted by NASA/MSFC for the purpose of establishing confidence in the data base from the lower temperature tunnel A.
Document ID
19850014155
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Marroquin, J. (Rockwell International Corp. Downey, Calif., United States)
Leef, C. R. (Rockwell International Corp. Downey, Calif., United States)
Date Acquired
September 5, 2013
Publication Date
March 1, 1985
Subject Category
Space Transportation
Report/Patent Number
DMS-DR-2520
NAS 1.26:167693
NASA-CR-167693
Accession Number
85N22466
Funding Number(s)
CONTRACT_GRANT: NAS9-17179
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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