本文针对采用振荡射流控制流动分离改善大攻角下翼型气动特性的问题,在NACA0015翼型上进行了多种工况的风洞实验.结果表明:在失速攻角附近,振荡射流抑制流动分离提高翼型升力系数的作用十分明显,可将翼型失速攻角推迟2°左右.存在最佳的振荡射流频率段、射流动量范围和射流位置,使得翼型性能的改善最大.实验还得到了振荡射流的频率、动量和施加位置等参数对翼型气动性能的影响规律.
参考文献
| [1] | Snel H.Review of the Present States of Rotor Aerodynamics[J].Wind Energy,1998(01):46-69. |
| [2] | Prandtl L.Essentials of Fluid Dynamics[M].北京:科学出版社,1974 |
| [3] | Zaman K B M Q .Effects of Acoustic Excitation on Stalled Flow Over an Airfoil[J].AIAA Journal,1992,30(06):1492-1499. |
| [4] | Collins F G;Zelenevitz J .Influence of Sound Upon Separated Flow Over Wings[J].AIAA Journal,1975,13(02):408-418. |
| [5] | Hsiao F B;Liu C F;Shyu R N .Control of Wall-Separated Flow by Internal Acoustic Excitation[J].AIAA Journal,1990,28(08):1440-1446. |
| [6] | Hsiao F B;Shyu R N .High Angle of Attack Airfoil Performance Improvement by Internal Acoustic Excitation[J].AIAA Journal,1994,32(03):655-662. |
| [7] | Seifert A;Bachar T .Oscillatory Blowing: A Tool to Delay Boundary-Layer Separation[J].AIAA Journal,1993,31(11):2052-2060. |
| [8] | Seifert A.;Wygnanski I.;Darabi A. .DELAY OF AIRFOIL STALL BY PERIODIC EXCITATION[J].Journal of aircraft,1996(4):691-698. |
| [9] | 程永卓,李宇红,唐进.振荡射流提高翼型升力的机理研究[J].工程热物理学报,2003(01):49-51. |
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