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Leeward centerline and side fuselage entry heating predictions for the space shuttle orbiterHeat transfer data measured along the leeward centerline and on the side fuselage of the Space Shuttle orbiter during STS-2 and STS-3 are compared with predictions of empirical heating techniques derived from wind tunnel tests. Steps required to extrapolate an existing leeward centerline theory to flight conditions are described. Generally favorable comparisons from Mach 24 down to approximately Mach 7 for both flights are presented. The side fuselage impingement heating method is currently under development, but some preliminary results are available. The method is briefly described and compared with wind tunnel and flight measurements. Side heating predictions are given for an STS-3 trajectory point near Mach 10 showing good agreement with flight data. There is evidence of embedded vortices emanating from the side fuselage impingement line which significantly enhance local heating rates at both wind tunnel and flight conditions.
Document ID
19840002089
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Helms, V. T., III (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 12, 2013
Publication Date
October 1, 1983
Publication Information
Publication: Shuttle Performance: Lessons Learned, Pt. 2
Subject Category
Space Transportation
Accession Number
84N10156
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19840002077Collected WorksShuttle Performance: Lessons Learned, Part 2
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