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Other TitleNumerical analysis on L/D augmentation of supersonic delta wing by using compression lift
Author(jpn)金森 正史; 今村 宰; 鈴木 宏二郎
Author(eng)Kanamori, Masashi; Imamura, Osamu; Suzuki, Kojiro
Author Affiliation(jpn)東京大学 大学院; 東京大学 大学院新領域創成科学研究科; 東京大学 大学院新領域創成科学研究科
Author Affiliation(eng)University of Tokyo Graduate School; University of Tokyo Graduate School of Frontier Sciences; University of Tokyo Graduate School of Frontier Sciences
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 page17
End page21
Publication date2008-02-29
AbstractWe numerically analyze supersonic flows around a delta wing with bent wing tip. The results show that the lift and drag forces decrease with the increase in the bending angle. But the local augmentation is observed around the hinge line of bending in the spanwise distribution. On the other hand, the lift-to-drag ratio keeps almost the same value independent of the bending angle. This phenomenon is significantly related to the interaction between shock waves generated at the wing root and tip. The mechanism of lift augmentation is explained as the 'compression lift' effect due to this shock-shock interaction.
DescriptionJAXA Special Publication
Keywordscompression lift; lift drag ratio; supersonic flow; delta wing; leading edge; separated flow; shock wave interaction; aerodynamic characteristic; aerodynamic coefficient; aircraft design; computational fluid dynamics; 圧縮揚力; 揚抗比; 超音速流; デルタ翼; 前縁; 剥離流; 衝撃波干渉; 空力特性; 空力係数; 航空機設計; 計算流体力学
Document TypeConference Paper
JAXA Category特別資料
Report NoJAXA-SP-07-016

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