School of Engineering, The University of Tokyo
Graduate School of Frontier Science, University of Tokyo
School of Engineering, The University of Tokyo
School of Engineering, The University of Tokyo
Graduate School of Frontier Science, University of Tokyo
18 June-19 June, 2009, Japan Aerospace Exploration Agency
抄録（英）
A new idea of an alternative aerodynamic control device for hypersonic vehicles utilizing plasma discharge is presented. The response of surface pressure distribution over a flat plate model to the D.C. plasma discharge in hypersonic flow was examined with both experiments and numerical analyses. It was revealed that the surface pressure upstream of the plasma area significantly increases, which would be applicable to a new aerodynamic control device. It was also found that there are two modes in the correlation between the electric power input and the surface pressure change around the plasma area. The burnt trace on the flat plate model after the experiments suggests that the pressure change may be caused by the onset of the boundary layer separation and the shock wave or compression wave formed in front of the separation bubble. Such pressure rise was also observed in the result of two-dimensional numerical analyses based on the Navier-Stokes equations with energy addition that simulates the Joule heating of plasma discharge. The steady-state solution shows that the pressure change observed in the experiments can be qualitatively explained as an effect of Joule heating on air flow.
内容記述
形態: カラー図版あり
内容記述（英）
Physical characteristics: Original contains color illustrations
放電プラズマによる極超音速での空力制御に関する基礎研究
64672004.pdf
(1.17MB)
