Abstract
Abstract : Results of an experimental investigation to determine the stagnation point velocity gradients for a family of blunt axisymmetric shapes at hypersonic Mach numbers are presented. Data presented in the form of model pressure distributions and stagnation point Mach number gradients are compared with existing data and theories. Although not accurately predicting the results, Newtonian theory is shown to provide a good basis for data correlation. Variations in model pressure distribution and stagnation point Mach number gradient from free-stream Mach number 6 to 10 were small and essentially within experimental precision. Model bluntness ranged from a hemisphere-cylinder to a flat-nose-cylinder, and data were obtained at free-stream Mach numbers 6, 8, and 10 and a nominal Reynolds number of 1,000,000, based on model diameter.
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