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采用5阶精度的加权紧致非线性格式(WCNS-E-5)数值模拟65°后掠角尖前缘三角翼的大攻角跨声速绕流流场,考察低耗散、高分辨率的WCNS-E-5格式对于三角翼涡破裂模拟的适用性,及激波旋涡干扰对涡破裂点位置的影响,重点研究三角翼大攻角旋涡破裂点的突然前移.通过求解任意坐标系下的非定常雷诺平均N-S方程,采用WCNS-E-5和SST两方程湍流模型,与试验结果和文献计算结果对比,表明既有高阶精度又能光滑捕捉激波的WCNS格式在模拟三角翼旋涡破裂方面具有一定优势,其数值结果与试验结果吻合较好,三角翼大攻角旋涡破裂点的突然前移是由于跨声速流场的激波旋涡干扰.
The fifth-order precision weighted nonlinear model (WCNS-E-5) was used to simulate the transonic flow field at a large angle of attack at a large angle of attack of the leading edge of a 65 ° sweep point. The effects of low dissipation, high resolution The applicability of the WCNS-E-5 scheme to the vortex rupture simulation of the delta wing and the influence of the shock of the shock wave on the location of the vortex rupture point are studied emphatically, and the sudden advance of the vortex rupture point at the high angle of attack of the delta wing is studied. By solving any arbitrary coordinate system The unsteady Reynolds averaged Navier-Stokes equations are compared with the experimental and literature results by using the WCNS-E-5 and SST turbulence models. It is shown that the WCNS scheme with both high-order precision and smooth shock capture can simulate the delta- The numerical results are in good agreement with the experimental results. The sudden advancement of the vortex rupture point at the large angle of attack of the delta wing is due to the shockwave interference across the transonic flow field.