TANGENTIAL MASS ADDITION FOR SHOCK BOUNDARY-LAYER INTERACTION CONTROL IN SCRAMJET INLETS

A series of tests are being performed to investigate and characterize shock-wave/boundary-layer interactions typical of hypersonic inlets and to develop methods of controlling, through the use of tangential mass addition, regions of shock-induced separation. The major objectives are being accomplished in a multiphase experimental test program with complementary application of computational techniques. Presented herein are results from the proof-of-concept phase of testing. The feasibility of using Mach 3 tangential air injection to eliminate separation associated with the cowl-shock/innerbody boundary-layer interaction in a scramjet inlet model has been demonstrated. The experimental test program was complemented by a computational investigation that demonstrated the importance of mass addition injector location relative to the shock/boundary-layer interaction region.