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Hypersonic shock tunnel heat transfer tests of the Space Shuttle SILTS pod configurationHeat transfer measurements have been made on a 0.0175-scale NASA Space Shuttle orbiter model having a simulated SILTS (Shuttle Infrared Leeside Temperature Sensor) pod on top of the vertical tail. Heat transfer distributions were measured both on the pod and on the vertical tail. The test program covered Mach numbers of 8, 11 and 16 in air, at Reynolds numbers from 100,000 to 18 million, based on model length. The angle of attack ranged from 30 deg to 40 deg at sideslip angles from -2 to +2 deg. Data were obtained with 92 thin film assistance thermometers located on the SILTS pod and on the upper 30 percent of the vertical tail. Heat transfer rates measured on the vertical tail show good agreement with flight data obtained from missions STS-1, -2 and -3. The variation of heat transfer to the pod with Reynolds number, Mach number and angle of attack is discussed.
Document ID
19830053703
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wittliff, C. E.
(Calspan Advanced Technology Center Buffalo, NY, United States)
Date Acquired
August 11, 2013
Publication Date
June 1, 1983
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 83-1535
Accession Number
83A34921
Funding Number(s)
CONTRACT_GRANT: NAS1-15948
Distribution Limits
Public
Copyright
Other

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