JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
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Other TitleExperimental study on interference flow of a supersonic Busemann biplane
Author(jpn)永井 大樹; 齋藤 賢一; 小川 俊広; 浅井 圭介
Author(eng)Nagai, Hiroki; Saito, Kenichi; Ogawa, Toshihiro; Asai, Keisuke
Author Affiliation(jpn)東北大学 大学院工学研究科; 東北大学 大学院工学研究科; 東北大学流体科学研究所; 東北大学 大学院工学研究科
Author Affiliation(eng)Tohoku University Graduate School of Engineering; Tohoku University Graduate School of Engineering; Institute of Fluid Science, Tohoku University; Tohoku University Graduate School of Engineering
Issue Date2008-02-29
PublisherJapan Aerospace Exploration Agency (JAXA)
Publication title第39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2007論文集
Proceedings of 39th Fluid Dynamics Conference/Aerospace Numerical Simulation Symposium 2007
Start page22
End page27
Publication date2008-02-29
AbstractAn interest in Busemann biplane has been revived and the feasibility of the supersonic biplane is now under investigation by many researchers. However, these studies are based mainly on CFD (Computational Fluid Dynamics) calculations and not validated by experiment so that a discussion on the wave cancellation mechanism between the two wings is very limited. The objective of this research is to measure the wing surface pressure distribution on a Busemann biplane and to study the two-dimensional interference phenomenon between the two wings. Since the Busemann biplane wings are so thin (the wing thickness ratio is 0.05) that it is difficult to install static pressure taps on the model. In this experiment, we used Pressure-Sensitive Paint (PSP) to measure surface pressure distributions on the model. PSP is an optical pressure measurement technique based on photochemical reaction called 'oxygen quenching'. This is a coating type sensor and considered only means to measure pressure fields on a thin airfoil model. In this study, wind tunnel experiment was conducted in a 60 mm x 60 mm indraft supersonic wind tunnel. The surface pressure distribution obtained using PSP were compared with CFD results and the Schlieren images. The complicated three-dimensional interference phenomenon between the two wings, including shock wave/boundary layer interactions was analyzed. On the basis of these experimental results, the wave cancellation mechanism of the Busemann biplane is discussed.
DescriptionJAXA Special Publication
KeywordsBusemann airfoil; biplane; supersonic aircraft; passenger aircraft; shock wave interaction; compression wave; wall pressure; pressure distribution; pressure measurement; pressure sensitive paint; supersonic wind tunnel; wind tunnel model; ブーゼマンエアフォイル; 複葉機; 超音速機; 旅客機; 衝撃波干渉; 圧縮波; 壁面圧; 圧力分布; 圧力測定; 感圧塗料; 超音速風洞; 風洞模型
Document TypeConference Paper
JAXA Category特別資料
Report NoJAXA-SP-07-016

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