MISC

2010年

Effects of plasma discharge on hypersonic flow over flat plate

41st AIAA Plasmadynamics and Lasers Conference
  • Yasumasa Watanabe
  • ,
  • Osamu Imamura
  • ,
  • Kojiro Suzuki

As a preliminary study on the application of plasma discharge to hypersonic aerodynamic control, the effect of direct current (DC) plasma in a hypersonic flow was examined with wind tunnel experiments. It was shown that the pressure rises significantly in the upstream region of the discharge. To the contrary, the pressure decreases in the region very close to the electrodes. This pressure change would be applied to a new aerodynamic control device. Under the assumption that the effects of the plasma discharge in a hypersonic flow are mainly due to the Joule heating, three-dimensional Navier-Stokes analyses were conducted. It was concluded that the pressure change far from the plasma area can be explained as an effect of the heat addition to the flow. © 2010 by the American Institute of Aeronautics and Astronautics, Inc.

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