Problems of Existence and Ambiguity of Solution at Asymmetrical Reflection of Steady Shocks

The asymmetric interaction of oblique steady shocks arising in supersonic flow through a narrowing channel between sharp wedges with different wedge angles, simulating the air intake of a jet engine of a high-speed aircraft, is studied. Numerical simulation of the interaction of incoming shocks with various intensities and slope angles is obtained. The results of calculations of the interaction of counter oblique shocks and gas flow beyond the interaction region are analyzed. The conditions of existence of regular and Mach (irregular) shock interaction of different intensity are examined. It is demonstrated that the irregular interaction of counter steady shocks can also occur when one of them stably reflects from the plane of symmetry only in a regular way.