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

Supersonic M(infinity) approximate to 4 flow past a slender sharp circular cone with semi- vertex angle theta(c) = 4 degrees. at small and moderate angles of attack is investigated both theoretically and experimentally over the Reynolds number range from 1.69 . 10(4) to 13.62 . 10(6). 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.