Hypersonic flow over a narrow delta plate at large angles of attack

The problem of hypersonic flow over a flat delta plate with a high sweepback anglex at angles of attack close to π/2 is solved using a numerical algorithm based on transition to the conical solution. The existence of conical flow atα ∼ π/2 with the velocity vector directed towards the apex of the plate is established. Values ofCp/sin2α and the thickness of the shock layer in the plane of symmetry of the plate are given as functions of the hypersonic similarity parameterk=tan α tanx. A comparison of the calculated and experimental data shows that they are in good agreement.