超声三速角翼背风区旋涡运动的数值模拟

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。

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

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.