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Computer programs for predicting supersonic and hypersonic interference flow fields and heatingThis report describes computer codes which calculate two-dimensional shock interference patterns. These codes compute the six types of interference flows as defined by Edney (Aeronaut. Res. Inst. of Sweden FAA Rep. 115). Results include properties of the inviscid flow field and the inviscid-viscous interaction at the surface along with peak pressure and peak heating at the impingement point.
Document ID
19730016558
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Morris, D. J. (NASA Langley Research Center Hampton, VA, United States)
Keyes, J. W. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 2, 2013
Publication Date
May 1, 1973
Subject Category
Fluid Mechanics
Report/Patent Number
L-8547
NASA-TM-X-2725
Accession Number
73N25285
Funding Number(s)
PROJECT: RTOP 501-06-08-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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