采用RANS方法实现三角翼前缘涡流场结构的数值模拟,计算采用全湍模式.通过数值模拟充分理解非尖前缘三角翼前缘涡的流场结构.数值模拟得到的三角翼表面压强分布与实验结果进行了对比,研究不同因素对三角翼前缘涡的影响.通过对比分析流场结构得到:尖前缘三角翼前缘涡是从机翼前缘拖出,分离位置固定；而钝前缘三角翼由于前缘分离点不固定,前缘涡流场结构变得更加复杂.对于钝前缘三角翼,当马赫数不变时,随着雷诺数的增加,三角翼前缘涡的分离被延迟.%The steady states of the discretized Reynolds average Navier-Stokes (RANS) equations are achieved for the numerical simulation of leading-edge vortex flow of delta wing.The calculations were performed with the assumption of fully turbulent flow.The overall goal is to understand more fully the flow topology for these non-sharp leading-edge delta wings.Comparisons between computational results and experiments are presented with regard to surface pressure coefficient and surface flow patterns for the suction side of the delta wing.Some factors affecting the vertical flow structures on delta wing are investigated thoroughly.Through analyzing and comparing the simulation results,it can be concluded that:The sharp leading edge shows the typical leading edge vortex beginning at the wing apex,but blunt-edged leading-edge separation is fundamentally more complex because primary separation is no longer affixed at the leading edge,the separation onset of blunt leading-edge varies with many parameters,such as Reynolds number and Mach number,etc.For the blunt leading-edge,an increase in Reynolds number,with Mach number held constant,was demonstrated to delay the onset of leading-edge vortex separation.
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