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Experimental pressure distributions for a family of blunt bodies at Mach numbers from 2.49 to 4.63 and angles of attack from 0 deg to 15 degPressure distributions for blunt body wind tunnel models at supersonic speeds and angles of attack from 0 to 15 degrees
Document ID
19690025922
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Howell, D. T. (NASA Langley Research Center Hampton, VA, United States)
Stallings, R. L., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 2, 2013
Publication Date
August 1, 1969
Subject Category
Aerodynamics
Report/Patent Number
NASA-TN-D-5392
Report Number: NASA-TN-D-5392
Accession Number
69N35300
Funding Number(s)
CONTRACT_GRANT: 124-07-17-02-23
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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