Influence of the angle of attack on the transition from a laminar to a turbulent boundary layer in the case of supersonic flow past sharp circular cones

Some results are given of an experimental investigation into the influence of the angle of attack on the transition in the symmetry plane of a sharp cone at Mach number M = 6.1. These results and available experimental data are used to establish the dependence of the transition Reynolds number on the angle of attack on the flow division line of sharp circular cones.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 4, pp. 160–163, July–August, 1982.