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在绕三角翼的跨声速流动中,随着迎角的增加,三角翼上的涡破裂位置会出现突然前移的现象。针对这一与亚声速下不同的流动现象,采用带曲率修正的Spalart-Allmaras(SAR)湍流模型,求解定常雷诺平均Navier-Stokes(RANS)方程,对不同迎角下绕65°后掠尖前缘三角翼的跨声速流动进行数值模拟,并在此基础上,采用基于SAR湍流模型的脱体涡模拟(DES)方法,对由激波干扰导致的前缘涡破裂位置的运动规律进行了初步探讨。模拟结果与试验结果对比表明:SAR湍流模型能准确地模拟出三角翼上的激波系统和旋涡结构,并能准确模拟出由于激波干扰导致的涡破裂位置突然前移的现象。此外,对涡破裂后流场的非定常数值研究发现,支架前端正激波的干扰作用使得涡破裂位置向下游移动比较突然,而向上游移动则相对缓慢。
In transonic flow around the delta wing, as the angle of attack increases, the vortex rupture position on the delta wing will suddenly move forward. Aiming to the different flow phenomena under subsonic velocities, the Spalart-Allmaras (SAR) turbulence model with curvature correction is used to solve the steady Reynolds-averaged Navier-Stokes (RANS) equation. On the basis of the numerical simulation of the transonic flow in the margin of the delta, the motion law of the vortex rupture at the leading edge caused by the shock wave is preliminarily studied by the DES method based on the SAR turbulence model Discussion. The simulation results show that the SAR turbulence model can accurately simulate the shock system and vortex structures on the delta wing and can accurately simulate the phenomenon of the sudden vortex rupture caused by the shock wave. In addition, the unsteady numerical study of the flow field after vortex rupture found that the disturbance of the forward shock of the front end of the vortex causes the location of vortex rupture to move abruptly downstream and relatively slow to the upstream.