For supersonic mixing enhancement, large scale stream-wise vortices seem to be the most advantageous. In SCRAM jet (supersonic combustion ramjet) engine, the device which introduces both the large scale stream-wise vortices and fuel into supersonic flow needs to be installed on the chamber wall to alleviate the heavy aerodynamic and heat load. So, it must have the high ability to mix the fluids in near-wall and free stream, efficiently. In the present study, we made effort to clarify the mixing performance of the Hyper-mixer type wall-mounted ramp injector, and we examined the effect of incoming boundary layer on supersonic mixing flow field which is generated by the Hyper-mixer type ramp injector.
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