可压缩机翼绕流的数值模拟及其稳定性分析  

Numerical Simulation of Compressible Flow Around the Airfoil and Its Stability Analysis

作　　者：贲安庆 窦华书[1] 

机构地区：[1]浙江理工大学机械与自动控制学院,杭州310018

出　　处：《浙江理工大学学报（自然科学版）》2015年第5期675-681,共7页Journal of Zhejiang Sci-Tech University(Natural Sciences)

基　　金：国家自然科学基金项目(51276142;51106141);浙江理工大学研究生创新项目(11130032661215)

摘　　要：运用数值模拟的方法分别模拟了马赫数为0.5、攻角为3和8的可压缩的机翼绕流流动,同时研究了马赫数为0.75、攻角为1.5,5和8的具有激波的可压缩流动机翼绕流,模拟结果与实验数据符合良好。采用能量梯度方法分析了流体流动的稳定性,研究发现:Spalart-Allmaras湍流模型能够准确反映出可压缩机翼绕流流动的流场特性;对于未产生激波的可压缩机翼绕流,背风的一侧首先发生失稳,且在机翼前端的上缘首先发生失稳;对于具有激波的机翼绕流,激波处的能量梯度最大,首先发生失稳。The compressible flows around an airfoil with the mach number of 0.5and angles of attack of 3and 8were simulated with numerical simulation.Meanwhile,the compressible flows around an airfoil with shock wave,the mach number of 0.75 and angles of attack of 1.5,5and 8 were studied.The simulation results well accorded with experimental data.Then the stability of fluid flow was analyzed with the energy gradient theory.It is found that Spalart-Allmaras turbulence model can accurately reflect flow characteristics of fluid flow.For compressible flow around an airfoil without shock wave,instability first appears at the leeward side and the upper edge of the front end of airfoil;for flow around an airfoil with shock wave,energy gradient at the shock wave reaches the maximum and instability happens first here.

关 键 词：可压缩 数值模拟 机翼绕流 能量梯度法 稳定性 

分 类 号：O355[理学—流体力学]