Abstract
For supersonic/hypersonic propulsion systems, the shock train in the inlet/isolator play a dominant role in compressing the incoming flow and providing suitable airflow to the engine. In this study, a detailed wind tunnel experimental study is performed in a supersonic isolator to investigate the potential of a micro-ramp as a form of shock train control. The results show that the micro-ramp modifies the structure of the shock train, inhibits the oscillation and upstream propagation of the shock train, and thus improves the total pressure recovery coefficient and safe working range of the hypersonic inlet/isolator.
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