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Improved Heat-Transfer Calculations for Hypersonic FlowLewis number corrected for extremely high airspeeds. Algorithm calculates improved, variable value of Lewis number, factor in equation for heat-transfer coefficient at stagnation point of body in hypersonic flow mach numbers of approximately 25. New algorithm improves accuracy of calculations of heat generated by hot air acting on moving body.
Document ID
19870000029
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Tech Brief
Authors
Greenschlag, S. N. (Rockwell International Corp.)
Date Acquired
August 13, 2013
Publication Date
January 1, 1987
Publication Information
Publication: NASA Tech Briefs
Volume: 11
Issue: 1
ISSN: 0145-319X
Subject Category
Mechanics
Report/Patent Number
MSC-20756
ISSN: 0145-319X
Report Number: MSC-20756
Accession Number
87B10029
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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