Abstract
Numerical approach for supersonic mixing flow field with the ramp injection is examined. It is said that ramp injector configurations can enhance mixing efficiency in combustor of ram/scram jet engine, by use of the formation of axial vortex. One of ramp injector types, which consists of alternate compression ramps and expansion troughs, has been studied by I.A. Waitz et al.. Calculation is conducted comparing with the result of the experimental study and calculated flow field was visualized by using particle traces.As a result of this numerical simulation, it was observed that the pattern of shock wave obtained by calculation agreed with experimental results. The formation of a counter-rotaing streamwise vortex pair and vortical roll-up of the jet were captured clearly as same as experimental observation. According to these results, it can be said that the CFD code used in this study has an ability to capture vortex structure formed by ramp injector and that the streamwise vortex generated by the injector is the one of key factors for enhancement of fuel-air mixing in scramjet combustor.
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