大攻角失速下翼型非线性颤振速度计算分析  

Computational analysis of airfoil nonlinear flutter velocity under conditions of stall with large angle of attack

作　　者：展志焕 顾超杰 胡盛靖 陈东阳 Zhan Zhihuan;Gu Chaojie;Hu Shengjing;Chen Dongyang(Beijing Research Institute of Mechanical&Electrical Technology,Beijing 100041,China;College of Electrical,Energy and Power Engineering,Yangzhou University,Yangzhou 225127,China)

机构地区：[1]北京机电工程研究所,北京430064 [2]扬州大学电气与能源动力工程学院,江苏扬州225127

出　　处：《南京理工大学学报》2021年第1期71-76,共6页Journal of Nanjing University of Science and Technology

基　　金：国家自然科学基金(12002301);江苏省自然科学基金(BK20190871)。

摘　　要：基于ONERA失速气动力模型,建立二元大攻角失速翼型非线性颤振运动的状态方程,通过龙格库塔法进行数值积分,获得二元翼型的非线性颤振时域响应曲线,并通过二分法寻找到失速翼型的颤振临界速度。仿真预测了半弦长对失速翼型气动弹性的影响规律,计算发现,随着半弦长的值变大,颤振速度会发生突跃,当弦长为0.5 m时,颤振速度最大,发生颤振的难度最大。Based on the ONERA aerodynamic stall model,the state equation of nonlinear flutter motion of a two-dimensional stall airfoil at large angle of attack is established.The nonlinear vibration response of the two-dimensional airfoil is obtained by numerical integration adopting Runge-Kutta method,and the flutter critical velocity of the stall airfoil is found using dichotomy method.Numerical simulations are carried out to predict the influence of half chord length on aeroelasticity of stall airfoil.The result shows that with the increase of half chord length,a sudden jump will occur to the flutter critical velocity.The flutter critical velocity comes to the peak when the chord length is 0.5 m and the flutter is the most difficult to happen.

关 键 词：ONERA失速气动力模型 二元翼型 颤振 时域分析 非线性 

分 类 号：TB122[理学—工程力学]