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通过求解三维定常雷诺时均方程,采用剪切应力输运(SST)湍流模型,在亚声速范围内,分别对融合体前体-三角翼组合体和旋成体前体-三角翼组合体流场中翼涡破裂现象进行了数值模拟。模拟结果显示:与旋成体前体相比,在中、大迎角时,融合体前体的分离涡,涡量集中、强度高,进入机翼上方流场后,能够与翼涡密切耦合,彻底地改变翼涡强度的分布状态,显著地延迟翼涡破裂。在此基础上,对融合体前体延迟翼涡破裂的机理进行了深入探讨。通过对模拟结果的对比分析,可得出下述结论:(1)机身前体横截面形状对翼涡强度的分布状态有着重大影响;(2)翼涡强度的分布状态对翼涡破裂位置有着重大影响,保持翼涡强度递增,有利于形成轴向顺压梯度,是延迟翼涡破裂的一个重要措施。
By solving the three-dimensional steady-state Reynolds-averaged equations, the shear stress transport (SST) turbulence model was used to simulate the flow field of the precursor-delta wing assembly and the spin-body precursor-delta wing assembly The mid-wing vortex rupture was numerically simulated. The simulation results show that the separation vortex and vorticity of the fusion precursor are concentrated and have high intensity at intermediate and high angles of attack compared with the precursor of the spinosome. When entering the flow field above the wing, the separation vortex and the vortices of the fusion precursor can be closely coupled, Completely change the distribution of the vortex strength, significantly delayed the vortex rupture. On this basis, the mechanism of delaying the vortex rupture of fusional precursors was discussed in depth. Through the comparative analysis of the simulation results, the following conclusions can be drawn: (1) The shape of the cross section of the fuselage body has a significant influence on the distribution of the vortex strength; (2) The distribution of the vortex strength has a significant influence on the vortex rupture position Has a significant impact, to maintain the strength of the wing vortex increases, is conducive to the formation of axial compressive gradient, is an important measure to delay the vortex rupture.