| 带扰流片的二维翼型非定常计算及分析 |
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| 引用本文： | 周涛,李晓勇.带扰流片的二维翼型非定常计算及分析[J].航空计算技术,2006,36(2):90-94. |
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| 作者姓名： | 周涛 李晓勇 |
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| 作者单位： | 中航第一飞机研究院,上海分院第一研究室,上海,200232 |
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| 摘 要： | 通过求解二维非定常可压N-S方程,研究了带扰流片的NACA0012翼型绕流问题.首先计算了扰流片固定在三个不同张开角度时的流动,气动力系数变化规律和已有实验数据对比,结论一致.并着重描述了扰流片张开时,背风区涡形成、发展和脱落过程,分析了非定常气动力产生的机理.为了进一步探讨振动扰流片对主翼的影响,采用Chimera重叠网格技术处理多体相对移动问题,分析了振动频率和振动幅度两个因素对时均气动力的影响.
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| 关 键 词： | 扰流片 非定常 N-S方程 |
| 文章编号： | 1671-654X(2006)02-0090-05 |
| 修稿时间： | 2005年11月26 |
Numerical Investigation of Unsteady Flow on Airfoil with a Spoiler |
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| ZHOU Tao,LI Xiao-yong.Numerical Investigation of Unsteady Flow on Airfoil with a Spoiler[J].Aeronautical Computer Technique,2006,36(2):90-94. |
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| Authors: | ZHOU Tao LI Xiao-yong |
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| Abstract: | Flow around NACA0012 airfoil with a stationary or oscillating spoiler has been simulated by solving the unsteady turbulent compressible two-dimensional Navier-Stokes equations.For the stationary spoiler,computations were carried out at three spoiler deflection angles.The results were consistent with the experimental data.To analyze the complex unsteady flow induced by the relative motion of several bodies,Chimera dynamic grid method has been applied to the oscillating spoiler problem.The frequency and the amplitude of the oscillating spoiler have been studied,and a conclusion has been drawn that the frequency and the amplitude can control the time-averaged lift and drag coefficients on main airfoil. |
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