Investigation of Flow Control for the Hypersonic Inlets via Counter Flow

Abstract EN

Experimental results show that there exist two flow fields in the hypersonicinlets when the forebody waves interact with the lip boundary, which is similar to the shock reflection ionhysteresis phenomenon.

In order to improve the performance of the flow field, counterflow is appliedto control the shock reflection configuration in the hypersonic inlets.

For better understanding of theinternal mechanism, inviscid numerical simulation is conducted.

And the results demonstrate that it isfeasible to realize the transition between the regular reflection configuration and the Mach reflection ionconfiguration in the hypersonic inlets.

That is because the von Neumann criterion and detachedcriterion play a dominant role, respectively, in these transitions.

In addition, the evolution process ofMach reflection ion in the hypersonic inlets can be divided into three stages: transmission of waves,emergence of Mach stem, and stabilization of flow field.