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An Investigation of the Pressure Distribution on a 1/15-Scale Model of the Lockheed WS-117L Vehicle Plus Booster "B" at Mach Numbers from 1.55 to 2.35Pressure coefficients were measured over the vehicle and over the forward part of the booster at Reynolds numbers of 3.0 x 10(exp 6) per foot. Tabular results are presented for two nose shapes at Mach numbers of 1.55, 1.75, 2.00, and 2.35, at angles of attack from -4 deg to +10 deg, and at 0 deg sideslip.
Document ID
19980231060
Acquisition Source
Headquarters
Document Type
Other - NASA Memorandum (MEMO)
Authors
Martin, Norman J. (NASA Ames Research Center Moffett Field, CA United States)
Date Acquired
September 6, 2013
Publication Date
March 1, 1959
Subject Category
Aerodynamics
Report/Patent Number
AF-AM-163
NASA-MEMO-3-13-59A
Report Number: AF-AM-163
Report Number: NASA-MEMO-3-13-59A
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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