Numerical method and results for inviscid supersonic flow over a compressive ramp

An algorithm is presented for the steady, two-dimensional, inviscid, supersonic flow near a wall with a compressive turn. The wall is contoured to provide a centered, Prandtl-Meyer compression. The focal point of the compression is the origin of an oblique shock wave, a slipstream and a secondary disturbance. This disturbance is an expansion, a weak solution oblique shock, or a strong solution oblique shock. Although algebraic equations govern the flow in the vicinity of the focal point, a sophisticated algorithm is required for the solution, which does not always exist and is not always unique. For a range of incident Mach numbers ranging from 1.2 to 16, the near-field solution is compared with its well-known asymptotic far-field counterpart.