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| 旋翼翼型低Ma数动态失速特性计算 | |
| 引用本文： | 谭剑锋,张呈林,王浩文,林永峰,邓景辉.旋翼翼型低Ma数动态失速特性计算[J].直升机技术,2009(2). |
| 作者姓名： | 谭剑锋 张呈林 王浩文 林永峰 邓景辉 |
| 作者单位： | 1. 南京航空航天大学航空宇航学院,南京,210016 2. 清华大学航天航空学院,北京,100084 3. 中国直升机设计研究所,景德镇,333001 |
| 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。 |
| 关 键 词： | 动态失速 低Ma数 旋翼 翼型 |
Computations of Unsteady Aerodynamic Characteristic of Rotor Airfoil at Low Mach Numbers |
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| Authors: | TAN Jianfeng ZHANG Chenglin WANG Haowen LIN Yongfeng DENG Jinghui |
| Institution: | 1.Nanjing University of Aeronautics & Astronautics; Nanjing; 210016; 2.School of Aerospace; Tsinghua Univesity; Beijing; 100084; 3.China Helicopter Research and Development Institute; Jingdezhen; 333001); |
| Abstract: | 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 experi... |
| Keywords: | dynamic stall low Mach number rotor airfoil |
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