To verify the flow control and drag reduction effects of plasma synthetic jets on supersonic flows, we fit the plasma thermodynamic properties and transport coefficients in the case of considering the thermally perfect gas effect, and use the energy source term model to simulate the typical flow field structures such as the supersonic flat plate and sphere, yielding consistent results with those of the experiment. The results show that the plasma synthetic jet can effectively disturb the development of the boundary layer and induce a series of large-scale structures for a supersonic flow of Mach number 2 over a plate; for a supersonic flow of Mach number 3 over a sphere, the plasma synthetic jet can significantly change the shock separation distance and the drag of the sphere. In the first cycle after discharge, the average drag of the sphere can be reduced by 6.3%, while the drag is reduced by 32.0% when the jet reaches a peak value, and the shock separation distance is increased by two times, realizing the expected effect of shock control and drag reduction.
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