| Item type |
紀要論文 / Departmental Bulletin Paper(1) |
| 公開日 |
2015-03-26 |
| タイトル |
|
|
タイトル |
Numerical Simulation of Separated Flows around a Wing Section at Steady and Unsteady Motion by a Discrete Vortex Method |
|
言語 |
en |
| 言語 |
|
|
言語 |
eng |
| 資源タイプ |
|
|
資源タイプ識別子 |
http://purl.org/coar/resource_type/c_6501 |
|
資源タイプ |
departmental bulletin paper |
| 著者 |
ASO, Shigeru
FUJIMOTO, Atsushi
FUTATSUDERA, Naoki
HAYASHI, Masanori
|
| 著者所属（英） |
|
|
|
en |
|
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Dept. Aeronautical Engineering, Kyushu University |
| 著者所属（英） |
|
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|
en |
|
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Dept. Aeronautical Engineering, Kyushu University |
| 著者所属（英） |
|
|
|
en |
|
|
Mitsubishi Heavy Industry, Co. Ltd. |
| 著者所属（英） |
|
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|
en |
|
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Nishinippon Institute of Technology |
| 出版者 |
|
|
出版者 |
宇宙科学研究所 |
| 出版者（英） |
|
|
出版者 |
Institute of Space and Astronautical Science |
| 書誌情報 |
en : The Institute of Space and Astronautical Science report. S.P. : The Proceedings of the Symposium on Mechanics for Space Flight 1989
巻 12,
p. 15-24,
発行日 1990-03
|
| 抄録（英） |
|
|
内容記述タイプ |
Other |
|
内容記述 |
Separated flows around a wing section at fixed attack angle of an oscillating airfoil are simulated numerically by a discrete vortex method combined with a panel method. The potettial flows around wing sections are expressed by vortex sheets and separated shear layers are expressed by discrete vortices. In the calculation a separation point is determined by solving boundary layer equation. The strength of shed vortex is estimated using local velocity near separation point. Also modification for the estimation of pressure coefficients around wing section are proposed. The estimated pressure distributions show good agreements with experimental results. Aerodynamic characteristics of a wing section of NACA4412 are predicted with excellent agreement with experiments. Also separated flows around pitching airfoils are simulated for various conditions. A hysteresis of lift of airfoil at dynamic stall is obtained. Further unsteady flow caused by abrupt change of the attack angle from 10 to 20 degrees is simulated numerically. The transient flow patterns show significant characteristics of unsteady flow. The hysteresis of the lift of piching airfoil is simulated properly. |
| ISSN |
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収録物識別子タイプ |
ISSN |
|
収録物識別子 |
0288-433X |
| 書誌レコードID |
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|
収録物識別子タイプ |
NCID |
|
収録物識別子 |
AA10455137 |
| 資料番号 |
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|
内容記述タイプ |
Other |
|
内容記述 |
資料番号: SA0033456000 |
SA0033456.pdf (659.6 kB)
