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Development of a method of analysis and computer program for calculating the inviscid flow about the windward surfaces of space shuttle configurations at large angles of attackA general method developed for the analysis of inviscid hypersonic shock layers is discussed for application to the case of the shuttle vehicle at high (65 deg) angle of attack. The associated extensive subsonic flow region caused convergence difficulties whose resolution is discussed. It is required that the solution be smoother than anticipated.
Document ID
19740019633
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Maslen, S. H. (Martin Marietta Labs. Baltimore, MD, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1974
Subject Category
Fluid Mechanics
Report/Patent Number
NASA-CR-132453
MML-TR-74-5C
Accession Number
74N27746
Funding Number(s)
CONTRACT_GRANT: NAS1-11604
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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