Unsteady Separation in Flare-Induced Hypersonic Shock-Wave Boundary-Layer Interaction Flowfield

摘要

the unsteadiness associated with the shock-wave boundary-layer interaction (SWBLI) flowfield on a HALIS axisymmetric configu- ration model is demonstrated in a Mach 9.68 flow with air as test gas. The SWBLI flowfield investigated generates high-pressure loads in The vicinity of separation and reattachment points. Near reattach- Ment the pressure on the flare approaches the stagnation point pres- Sure level. Off-surface flow study using the laser schlieren system Revealed increased energy levels near the separation point suggesting Random fluctuations in the instantaneous position of the separation Shock.