Abstract
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.
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