@inproceedings{oai:jaxa.repo.nii.ac.jp:00004902,
 author = {渡邉, 保真 and 高間, 良樹 and 今村, 宰 and 綿貫, 忠晴 and 鈴木, 宏二郎 and Watanabe, Yasumasa and Takama, Yoshiki and Imamura, Osamu and Watanuki, Tadaharu and Suzuki, Kojiro},
 book = {宇宙航空研究開発機構特別資料: 第41回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2009論文集, JAXA Special Publication: Proceedings fo 41st Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2009},
 month = {Feb},
 note = {平成21年6月18-19日. 宇宙航空研究開発機構調布航空宇宙センター, 18 June-19 June, 2009, Japan Aerospace Exploration Agency, 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., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0064672004, レポート番号: JAXA-SP-09-011},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {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},
 volume = {JAXA-SP-09-011},
 year = {2010}
}