超临界翼型跨声速抖振载荷问题数值模拟研究  

Numerical Research on the Transonic Buffet Loads of A Supercritical Airfoil

作　　者：李强[1] 操小龙[1] 刘毅[2] 王刚[2] Li Qiang;Cao Xiaolong;Liu Yi;Wang Gang(Beijing Electro-mechanical Engineering Institute,Beijing 100074,China;National Key Laboratory of Aerodynamic Design and Research,NWPU,Xihn 710072,China)

机构地区：[1]北京机电工程研究所,北京100074 [2]西北工业大学翼型叶栅空气动力学国防科技重点实验室,西安710072

出　　处：《战术导弹技术》2018年第6期44-51,共8页Tactical Missile Technology

基　　金：国防基础科研项目(A0420132307)

摘　　要：采用非定常雷诺数平均数值模拟方法(Unsteady Reynolds Averaged Navier Stokes,URANS)及脱体涡数值模拟方法(Detached Eddy Simulation,DES)模拟了OAT15A超临界翼型跨声速绕流流场,分别从抖振边界和脉动压力预测两方面来研究其流动特性,并与实验值进行了对比。计算结果表明,抖振边界同激波位置与上翼面最大曲率点的间距密切相关,抖振状态出现在激波位置足够靠近该曲率最大点。URANS及DES湍流模型均能捕捉到激波抖振,DES方法得到的脉动压力系数更接近实验值,而URANS方法得到的基频更为接近。The transonic flow on the OAT15 A supercritical airfoil is simulated by using the URANS( Unsteady-Reynolds-Averaged Navier-Stokes) and DES( Detached-Eddy-Simulation) methods. The features of flow field,including the buffet boundary and the fluctuating pressure,are researched and compared with experimental results. Numerical results show that,the buffet boundary is closely related with the distance between shock wave and the maximum-curvature point on the upper surface of the wing,and buffet appears when the shock wave is close enough to the maximum-curvature point. Shock-wave oscillation is observed in both simulations which use the URANS and DES methods respectively. The root-mean-square value of the fluctuating pressure is closer to the experimental results by using the DES method,while a closer basic frequency is obtained with URANS method.

关 键 词：抖振 抖振边界 脉动压力 DES 跨声速 

分 类 号：O354.2[理学—流体力学]