Heat Transfer and Pressure Measurement on a Concave Conic Model under Both Steady and Unsteady Hypersonic Flow Conditions.

摘要

Heat transfer and pressure measurements have been measured on a conic configuration with a strongly concave surface and a blunt nose tip in the von Karman Institute Longshot free piston tunnel at M-15 and 20. The test flow parameters achieved closely simulated reentry aerodynamic conditions. Information derived from the measurements and also from high speed cine schlieren sequences enabled information to be derived on the effect of Mach number, Reynolds number, surface roughness and flow incidence on the flow over the model, the heat transfer distribution and stability of the flow. (Author)