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An Improved Dynamic Stall Model for Rotor Airfoil Based on Experimental Investigations

机译：基于实验研究的改进型转子翼型失速模型

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摘要

The dynamic stall characteristics of rotor airfoil have remarkable effects on helicopter performances.rnTherefore, a lot of investigations have been conducted in the middle of the 20th century, and thisrnphenomenon is still a hot issue in the field of helicopter technology. For the engineering applications, manyrnsemi-empirical models for dynamic stall have been established, one of the best models named Leishman-rnBeddoes (L-B) model is adopted by most researchers since it has fewer parameters and definite physicsrnmeaning. However the L-B model could not accurately simulate the normal force when the reattachingrnphenomenon of airflow over airfoil occurs. To overcome this shortcoming, an experiment about airfoilrndynamic stall was designed in this paper. Using the PIV measuring technology, the dynamic stallrncharacteristics of the typical rotor airfoil SC1095 and NACA0012 were measured with different conditions,rnand then the moving velocity of leading edge vortex was calculated based on the measurement. Comparingrnwith free stream velocity, a new rule about the moving velocity of leading edge vortex is observed andrnanalyzed. As a result, it provides a basis to modify the classical L-B model. Comparing with the classicalrnmodel, the peak of airfoil normal force coefficient calculated by the modified model is increased about 5%,rnand the negative peak of moment coefficient is promoted about 13%, both of these have better agreementsrnwith the experimental data.
机译：旋翼机翼的动态失速特性对直升机的性能有显着影响。因此，在20世纪中叶进行了许多研究，这种现象仍然是直升机技术领域的一个热门问题。对于工程应用，已经建立了许多动态失速的半经验模型，由于其参数少，物理意义明确，因此被大多数研究者采用的最好的模型之一称为利什曼-贝德多斯（L-B）模型。然而，当翼型上的气流发生重新附着现象时，L-B模型无法准确地模拟法向力。为了克服这个缺点，本文设计了一个关于翼型动力失速的实验。利用PIV测量技术，在不同条件下测量了典型转子翼型SC1095和NACA0012的动态失速特性，然后根据测量结果计算了前缘涡旋的运动速度。与自由流速度比较，观察并分析了有关前缘涡旋运动速度的新规律。因此，它为修改经典L-B模型提供了基础。与经典模型相比，改进模型计算得到的翼型法向力系数峰值增加了约5％，弯矩系数的负峰值提高了约13％，两者与实验数据具有较好的一致性。

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  • 会议地点 Tianjin(CN)
  • 作者

    Wang Qing; Zhao Qi-jun; Zhao Guo-qing;

  • 作者单位

    National Key Laboratory of Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics,Nanjing, 210016, ChinaTele: 086-025-84893753e-mail: mingqingwq@nuaa.edu.cn;

    National Key Laboratory of Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics,Nanjing, 210016, China;

    National Key Laboratory of Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics,Nanjing, 210016, China;

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