三角翼大攻角绕流数值模拟研究  

NUMERICAL SIMULATION OF THE FLOWFIELD OVER DELTA WING AT HIGH ANGLE OF ATTACK

作　　者：白鹏[1] 周伟江[1] 汪翼云[1] 

机构地区：[1]北京空气动力研究所

出　　处：《航空学报》1999年第3期254-257,共4页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金

摘　　要：采用Ｈａｒｔｅｎ－Ｙｅｅ的二阶精度隐式ＴＶＤ格式对Ｎ－Ｓ方程进行数值模拟，研究了后掠角为６５°和７０°的三角翼绕流的流场特性。计算结果表明：ＴＶＤ格式中限制器函数的选取对于三角翼绕流结构的计算结果具有较重要的影响。结合张涵信的旋涡定性分析理论对旋涡的发展过程进行研究，此外，还对二次涡破裂现象和网格分布影响等问题进行了探讨。The flow over delta wing with 65° and 70° swept at high angle of attack is investigated by solving the three dimensional, compressible Navier Stokes equations utilizing the second order upwind TVD algorithm(Harten Yee).The calculated results indicate that the choice of the limiter function in TVD scheme has an important influence on the numerical simulation which is carried out on the delta wing flow structure. The development of vortex is studied with ZHANG Han xin′s vortex analysis theory. In addition, the second vortex breakdown performance and the grid influence are discussed in this article.

关 键 词：三角翼 分离流 数值方法 极限环 大攻角 绕流 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程] V211.3