马赫数和雷诺数对钝前缘三角翼流场的影响  

Numerical Simulation for Effects of Mach and Reynolds Number on Flow over Medium Radius Leading Edge Delta Wing

作　　者：顾祥玉[1] 杨永[1] 李喜乐[1] 

机构地区：[1]西北工业大学翼型叶栅空气动力学国防科技重点实验室,陕西西安710072

出　　处：《航空计算技术》2012年第6期13-16,共4页Aeronautical Computing Technique

基　　金：国家自然科学基金项目资助(11002117)

摘　　要：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。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 multivortexes 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 leadingedge vortex separation and the multivortexes move inboard, whereas the increment of Reynolds number postpones it and the location of vortexes move outboard correspondingly.

关 键 词：RANS 三角翼 钝前缘 马赫数 雷诺数 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]