Theoretical and Experimental Investigation of Supersonic Flow Past a Slender Sharp Circular Cone at Incidence

Abstract

Supersonic M∞≈4 flow past a slender sharp circular cone with semi-vertex angle θc=4° at small and moderate angles of attack is investigated both theoretically and experimentally over the Reynolds number range from 1.69·104 to 13.62·106. The theoretical analysis is based on the numerical integration of the three-dimensional Navier-Stokes and Reynolds equations, while the experimental study was carried out in a wind tunnel of the Central Aerohydrodynamics Institute (TsAGI). The calculated and measured integral characteristics of the cone are compared.