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Flow fields over sharp edged delta wings with attached shocksAnalysis of supersonic and hypersonic flow of inviscid ideal gas over conical wings with sharp leading edges and attached shock waves by three dimensional method of characteristics
Document ID
19710013196
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Beeman, E. R., Jr. (Northrop Corp. Hawthorne, CA, United States)
Powers, S. A. (Northrop Corp. Hawthorne, CA, United States)
Date Acquired
August 6, 2013
Publication Date
April 1, 1971
Publication Information
Publisher: NASA
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-1738
Report Number: NASA-CR-1738
Accession Number
71N22672
Funding Number(s)
CONTRACT_GRANT: NAS1-7850
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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