Hypersonic Flow over a Yawed Circular Cone

Abstract

A 10° semi-apex, circular cone is tested in air at Mach 8 and at 0 yaw angles to 24°; surface pressure, heat transfer, and pitot-pressure throughout the flow field are presented. The nominal surface temperature is 40" of the free stream stagnation temperature, and the Reynolds nunber, based on cone generator length, is varied from 0.5 x 10^5 to 4.2 x 10^5 . Heat transfer is measured at higher surface temperature ratios (up to 56%) and Reynolds nunbers (up to 7.3 x 10^5) by reducing the free stream stagnation temperature. All raw data consist of continuous circumferential distributions of each quantity and are included in a supplement. The surface pressure data are compared with the theories of Stone-Kopal and Cheng; Reshotko's theory of heat transfer to the windward generator is compared with experiment. The probe data delineate the boundary between viscous and inviscid flow and determine the shape of the outer shock wave as well as the secondary shocks which appear in the flow field at large yaw. The probe data are sufficient to determine the flow field in the plane of symmetry and permit an approximate representation of the Mach number profiles of the separated viscous flow in the leeward meridian plane beyond a moderate yaw angle.