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An Experimental Investigation of the Pressure Distribution on A 1/15-Scale Model of the Lockheed WS-117L Vehicle Plus Booster "B" at Mach Numbers from 0.70 to 1.45Results obtained with two nose shapes tested at a Reynolds number per foot of 5 x 10(exp 6) at angles of attack from -4 deg to +10 deg at 0 deg angle of sideslip are presented in tabulated pressure coefficient form without analysis.
Document ID
19980231065
Acquisition Source
Headquarters
Document Type
Other - NASA Memorandum (MEMO)
Authors
Fahey, Russell E. (NASA Ames Research Center Moffett Field, CA United States)
Marker, Ralph D. (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-3-12-59A
A-217
Report Number: AF-AM-163
Report Number: NASA-MEMO-3-12-59A
Report Number: A-217
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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