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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

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

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