RANS method based on S- A model isused to simulate the flow over medium radius leading edge 65°delta wing configuration in different Mach and Reynolds number. Details of the medium radius delta wing multi - vortexes structure and the progression of flow are discussed and analyzed; comparison between numerical solution and the experiment data of DLR and NASA was presented. It shows that in medium attack angle the surface pressure coefficient is matched quite well;the increment of Mach number promotes the leading- edge vortex separation and the multi- vortexes move inboard,whereas the increment of Reynolds number postpones it and the location of vortexes move outboard correspondingly.%基于Spalart-Allmaras(SA)湍流模型,求解定常RANS方程,数值模拟后掠角为65°的钝前缘三角翼的亚音速流场.分析不同雷诺数、马赫数下钝前缘三角翼上表面的复杂涡系结构及其发展过程,并与实验结果进行了对比.计算结果表明:在中度迎角下,所得的各弦向站位的物面压力系数与实验数据吻合良好；随着雷诺数的增加,三角翼前缘流动分离位置后移,其背风面涡系向内移动；而马赫数的增加则导致分离位置前移,背风面涡系向外移动.
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