Theoretical Prediction of Pressures in Hypersonic Flow with Special Referencce to Configurations Having Attached Leading Edges Shock: Part II. Experimental Pressure Measurements at Mach 5 and 8

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Report Number: ASD TR 61-60 Part 2
Author(s): Mead, Harold R., Koch, Frank
Corporate Author(s): Grumman Aircraft Engineering Corporation
Laboratory: Flight Control Laboratory
Date of Publication: 1962-05
Pages: 169
Contract: AF 33(616)-6400
DoD Project: 8219
DoD Task: 82159
Identifier: AD0282301

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Provenance: AFRL/VACA

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