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64672004.pdf1.15 MB
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
Other TitlePreliminary Studies on Aerodynamic Control with Direct Current Discharge
Author(jpn)渡邉, 保真; 高間, 良樹; 今村, 宰; 綿貫, 忠晴; 鈴木, 宏二郎
Author(eng)Watanabe, Yasumasa; Takama, Yoshiki; Imamura, Osamu; Watanuki, Tadaharu; Suzuki, Kojiro
Author Affiliation(jpn)東京大学大学院工学系研究科; 東京大学大学院新領域創成科学研究科; 東京大学大学院工学系研究科; 東京大学大学院工学系研究科; 東京大学大学院新領域創成科学研究科
Author Affiliation(eng)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
Issue Date2010-02-26
PublisherJapan Aerospace Exploration Agency (JAXA)
宇宙航空研究開発機構
Publication titleJAXA special publication: Proceedings fo 41st Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2009
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
VolumeJAXA-SP-09-011
Publication date2010-02-26
Languagejpn
eng
AbstractA 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.
DescriptionOriginal contains color illustrations
Meeting Information: 18 June-19 June, 2009, Japan Aerospace Exploration Agency
形態: カラー図版あり
会議情報: 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
Document TypeConference Paper
JAXA Category特別資料
ISSN1349-113X
NCIDAA11609371
SHI-NOAA0064672004
Report NoJAXA-SP-09-011
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/14208


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