Experimental and numerical study of a hypersonic separated flow in the vicinity of a cone-flare model

An axisymmetric laminar separated flow in the vicinity of a cone-flare model is studied experimentally and numerically for a Mach number $\mathrm{M} = 6$. The distributions of pressure and Stanton numbers along the model surface and velocity profiles in the region of shock wave–boundary layer interaction are measured and compared with the calculated data. The influence of the laminar–turbulent transition on flow parameters is studied numerically.