基于DES方法的三角翼激波-涡干扰流场数值模拟

采用基于Spalart-Allmaras湍流模型的脱体涡模拟（DES）方法,数值求解Navier-Stokes方程,模拟绕尖前缘三角翼的跨音速流动,并对三角翼上翼面的复杂激波-旋涡干扰流场进行了分析。与NASA兰利研究中心的NTF风洞实验结果对比分析表明,DES方法能很好地模拟跨音速三角翼上的旋涡流动。随着攻角由中度攻角增加到大攻角,支架附近的激波越来越强,对主分离涡的干扰作用越来越大,直至出现激波干扰导致的涡破裂。激波的形状、位置及涡破裂位置均与实验结果吻合良好。

Numerical Simulation of Transonic Shock-vortex Interaction Flow on Delta Wing Using DES

A transonic flow around delta wing with sharp leading edge is simulated by detached eddy simulation（DES）method and the complex shock-vortex interference flow field on the top surface of delta wing is analysed.It is shown in the result that the DES method can simulate the vorticity flow over the top surface of transonic delta wing well by comparing with the experimental data in NASA Langley Research Center.The shock wave around the sting becomes stronger and stronger as the angle of attack increases from middle angle to high angle.The shock wave′s interference to the primary separation vortices becomes more obvious until the vortex breakdown caused by these shock waves.It is shown that both the shape and the location of the shock wave is the same as the experimental data.The location where the vortex breaks is also well accord with the experimental data.