The structure of supersonic mixing flow field in ram/scramjet combustor was investigated numerically and experimentally. One type of parallel injection method with a ramp injector was selected and the effects of oblique shock impingement on the mixing layer generated from the ramp had been studied. The wedge angle of the shock-generator and the distance from the injection plane to the leading edge of it were varied parametrically. The pattern of shock waves and the flow pattern on the wall surface were visualized in the experiments. The numerical results of those flow pattern images had a good agreement with the results. Also, comparisons of static pressure on the wall surface showed good agreement qualitatively. Numerical results captured the structures of vortical flow field clearly. It was shown that the impingement of oblique shocks made streamwise vorticies strongly and the wedge angle of the shock-generator was more effective to enhance vorticity of the streamwise vorticies.
