| 旋翼翼型低Ma数动态失速特性计算 | |
| 谭剑锋 ; 张呈林 ; 王浩文 ; 林永峰 ; 邓景辉 ; TAN Jianfeng ; ZHANG Chenglin ; WANG Haowen ; LIN Yongfeng ; DENG Jinghui | |
| 2010-06-07 ; 2010-06-07 | |
| 关键词 | 动态失速 低Ma数 旋翼 翼型 dynamic stall low Mach number rotor airfoil V211.52 |
| 其他题名 | Computations of Unsteady Aerodynamic Characteristic of Rotor Airfoil at Low Mach Numbers |
| 中文摘要 | 低Ma数下,翼型前缘涡强度的增加和移动使法向力系数产生很大的超调量,Beddoes通过增加一项与延迟后后缘分离点有关项来模拟该特性,并改进Leishman-Beddoes二维翼型动态失速模型。在此基础上,本文在非定常法向力系数中引入一阶延迟,推迟失速判断点,得到修正后模型;而后,通过计算NACA0012、OA207翼型在低Ma数下的非定常气动力,并与实验结果进行对比,验证了模型在计算翼型低Ma数下非定常气动力的准确性,并分析了折合频率、迎角平均值、振幅对计算结果的影响。; At low Mach number,an overshoot in normal force occurs due to the leading-edge vortex growing in strength and convecting,Beddoes simulate the characteristic and improve Leishman-Beddoes dynamic-stall model by adding a function of delayed separation location.Base on the improvement,the dynamic-stall model was modified by delaying the non-steady normal force and stall onset.Then,the normal force and pitching moment on NACA0012,OA207 airfoil at low Mach number were calculated and compared with available experimental data to validate the reliability of modification,the influence of reduced frequency,average and extent of pitch is also simply investigated and attain some conclusions. |
| 语种 | 中文 ; 中文 |
| 内容类型 | 期刊论文 |
| 源URL | [http://hdl.handle.net/123456789/37622]  |
| 专题 | 清华大学 |
| 推荐引用方式 GB/T 7714 | 谭剑锋,张呈林,王浩文,等. 旋翼翼型低Ma数动态失速特性计算[J],2010, 2010. |
| APA | 谭剑锋.,张呈林.,王浩文.,林永峰.,邓景辉.,...&DENG Jinghui.(2010).旋翼翼型低Ma数动态失速特性计算.. |
| MLA | 谭剑锋,et al."旋翼翼型低Ma数动态失速特性计算".(2010). |
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