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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2021, Vol. 42 ›› Issue (7): 124773-124773.doi: 10.7527/S1000-6893.2020.24773

• Fluid Mechanics and Flight Mechanics • Previous Articles     Next Articles

Bow shock wave control and drag reduction by plasma synthetic jet

CHEN Jiazheng1, HU Guotun2, FAN Guochao1, CHEN Weifang1   

  1. 1. School of Aeronautics and Astronautics, Zhejiang University, Hangzhou 310027, China;
    2. Research and Development Center, China Academy of Launch Vehicle Technology, Beijing 100076, China
  • Received:2020-09-21 Revised:2020-09-30 Published:2020-11-27
  • Supported by:
    National Natural Science Foundation of China (6162790014)

Abstract: 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.

Key words: plasma synthetic jet, energy source term model, supersonic flow, flow control, drag reduction

CLC Number: