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47401000.pdf9.15 MB
Other TitleEffect of sidewall configurations on aerodynamic performance of supersonic air-intake
Author(jpn)渡辺 安; 村上 哲; 藤原 仁志
Author(eng)Watanabe, Yasushi; Murakami, Akira; Fujiwara, Hitoshi
Author Affiliation(jpn)宇宙航空研究開発機構 総合技術研究本部; 宇宙航空研究開発機構 総合技術研究本部; 宇宙航空研究開発機構 総合技術研究本部
Author Affiliation(eng)Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics; Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics; Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Issue Date2004-03-25
PublisherJapan Aerospace Exploration Agency (JAXA)
Publication date2004-03-25
AbstractThe effects of sidewall configurations on the aerodynamic performance of two dimensional external compression supersonic air-intakes were investigated experimentally and numerically. The aerodynamic performance for various yaw angles and ramp angles was obtained by wind tunnel tests performed in the Mach number range of 1.5 to 2.0. It was found that the major advantage of an air-intake with a larger sidewall configuration is its wider stable range in subcritical operation. On the other hand, it also had the disadvantages of lower pressure recovery and larger spatial distortion, especially in supercritical operation, both of which were due to boundary layer separation in the subsonic diffuser. CFD results made it clear that the ingestion of the shear layer caused by shock-shock interaction occurred at a higher mass flow ratio in the smaller sidewall configuration, due to the change in the shape of the captured stream tube, which in turn is due to the increase in sideways spillage. It was also found that boundary layer separation in the subsonic diffuser depended on the shape factor of the boundary layer coming into the subsonic diffuser, which is affected by the interaction of the boundary layer on the sidewall surface with the shock system.
DescriptionJAXA Research and Development Report
Keywordssupersonic flow; supersonic flight; air intake; aerodynamic characteristic; sidewall configuration; wind tunnel test; supersonic wind tunnel; CFD; 超音速流; 超音速飛行; エアインテーク; 空力特性; 側壁形状; 風洞試験; 超音速風洞; CFD
Document TypeTechnical Report
JAXA Category研究開発報告
Report NoJAXA-RR-03-009

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