Pressure distributions and shock shapes for cylindrical afterbodies were calculated by using method of characteristics for air and helium and Mach number range from 5 to 40; flow parameters obtained from blast wave theory give good correlations of blunt nose induced pressures and shock shapes; concept of hypersonic similitude enables good correlation of results with respect to body shape, Mach number, and ratio of specific heats.
Analytic study of induced pressure on long bodies of revolution with varying nose bluntness at hypersonic speeds
NASA -- Tech Report
1960
37 pages
Report
Englisch
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