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NAOSITE : Nagasaki University's Academic Output SITE > Faculty of Engineering > Bulletin > Reports of the Faculty of Engineering, Nagasaki University > Volume 29, No. 53 >


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Title: 翼型翼に発達する層流境界層の解析
Other Titles: Investigation of Laminar Boundary Layer on Airfoil
Authors: 林, 秀千人 / 佐々木, 壮一 / 児玉, 好雄 / 清水, 光昭
Authors (alternative): Hayashi, Hidechito / Sasaki, Soichi / Kodama, Yoshio / Shimizu, Mitsuaki
Issue Date: Jul-1999
Citation: 長崎大学工学部研究報告 Vol.29(53) p.167-172, 1999
Abstract: The development of the laminar boundary layer on the NACA symmetrical airfoils and the separation of it are simulated by using the boundary layer theory and discrete vortex method. The arrangement of the discrete vortices on the airfoil affects on the separation position very much because the separation is sensitive to the velocity gradient of the main flow. It needs the very small increment 1/500 in boundary layer simulation to get the exact position of the separation. The simulation of both methods makes the good results compared with the experiments.
URI: http://hdl.handle.net/10069/5069
ISSN: 02860902
Type: Departmental Bulletin Paper
Appears in Collections:Volume 29, No. 53

Citable URI : http://hdl.handle.net/10069/5069

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