Experimental Study of the Hypersonic Flow Over Convex Conic Model Resembling the Nosetip of a Reentry Vehicle.

摘要

Heat transfer and pressure measurements have been measured on a convex conic configuration with a spherical nosetip in the von Karman Institute Longshot free pison tunnel at M=15 and 20. The test flow parameters achieved closely simulated reentry aerodynamic conditions. Information derived from the measurements and also from schlieren photographs enabled statements to be made on the effect of Mach number, Re number, surface roughness and flow incidence on the flow over the model. (Author)