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 1.45.

Author: Fahey, Russell E.
Published: Mar. 1959.
Physical Description: 1 electronic document
Additional Creators: Marker, Ralph D.

Online Version

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Summary

Results 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.

Other Subject(s)

Aerodynamics

Collection

NASA Technical Reports Server (NTRS) Collection.

Note

Document ID: 19980231065.
AF-AM-163.
A-217.
NASA-MEMO-3-12-59A.

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