超声三速角翼背风区旋涡运动的数值模拟  

Numerical Simulation of Vortex Structure in the Leeside of Supersonic Delta Wing

作　　者：张树海[1] 张涵信[1] 朱国林[1] 

机构地区：[1]中国空气动力研究与发展中心

出　　处：《空气动力学学报》1996年第4期430-435,共6页Acta Aerodynamica Sinica

基　　金：国家自然科学基金

摘　　要：本文采用杂交通量分裂的ＮＮＤ格式模拟了Ｍ∞＝１．９５、Ｒｅ＝９．５×１０５，α＝１０°、２０°的三角翼绕流流场，结果揭示了超声速旋涡沿其自身轴线的发展规律，当旋涡轴向速度为超声速且处于顺压区时，涡轴附近的横截面流线向外转，而由机翼前缘尖点处发出的截面流线向内卷，它们之间存在极限环。数值结果与张涵信的拓扑分析结果完全一致。Steady solutions of supersonic flow over a sharp-edged delta wing for moderate and high angles of attack are obtained numerically by solving the compressible Navier-Stokes equation using NND scheme with mixed flux splitting method. The results show that when the axial velocity along the axis of vortex is supersonic and the pressure is favorable, the cross streamlines near the axis are outward. Since the cross streamlines starting from the sharp edge are inward, a limit cycle exists between them.The calculated flow parttern agrees well with the topological results given by Zhang Hanxin.

关 键 词：NND格式 机翼空气动力学 三角翼 

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]