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

Supersonic M4 flow past a slender sharp circular cone with semi-vertex angle _c=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.