三角翼大迎角绕流数值模拟的网格影响研究
首发时间:2010-03-01
摘要:通过求解层流假设的N-S方程,对三角翼大迎角绕流进行了一系列的数值模拟。在综合考虑气动力系数以及表面压力分布和涡核轴向速度等流场细节的基础上,探讨计算网格对模拟效果的影响。结果表明,不同远场边界位置对计算结果没有影响,在上翼面法向加密网格比在边界层内加密网格更能够获得精确的模拟结果,局部网格加密也能进一步改善结果。应用改进后的网格对70°后掠角三角翼的旋涡流动进行模拟,得到了气动力特性和旋涡特性的分析结论。
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Grid influence in computing the aerodynamics of delta wing at high angle of attack
Abstract:The vortical flow over a delta wing at high angle of attack has been investigated numerically using laminar N-S method. The accuracy of the aerodynamic coefficients, the surface pressure distribution and the axial velocity along the vortex core has been studied to discuss the influence of different grids. The results indicated that the different far-field boundary locations did not have any noticeable effect on the numerical simulation results, the accuracy of the results can be improved by placing more grid points in the normal direction over the upper surface of the delta wing, rather than by placing more points in the boundary layer. The aerodynamic characteristics and vortex features of a delta wing of 70o leading-edge sweep have been analysised using the improved grid.
Keywords: delta wing numerical simulation grid vortex features
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