关键词: 流动显示, 旋涡激波, 边界层分离

Abstract: This paper describes a flow visualization experiment over the leeside of a slender tapered wing with a leading edge sweepback angle of 65° and a biconvex section. By using laser vapor screen, schlieren and oil flow techniques, the test was carried out at Mach numbers of 1.10, 1.53, 2.53, 3.01 and 4.01 for angles of attack from 5° through 25°. And photos of flow off body and on lee surface have been taken. The vapor screen photos show seven distinct types of flow developed over the delta region of the wing. These types of flow are displayed in a plane of Mach number and angle of attack normal to the leading edge. In the region of the side edge there are side vortices formed and in the region of the trailing edge trailing vortices shed. The variations of both the bow shock positions at different Mach numbers and the positions of separating lines induced by shock waves with Mach numbers and angles of attack are obtained based upon the schlieren plus the vapor screen photos in the sections. The oil flow visualization shows clearly primary reattachment, secondary separation, secondary reattachment lines and side edge vortices on the lee surface. The results of this test are in good agreement with experiments and numerical simulations of others.

Key words: flow visualization　vortices, shock waves, boundary layer separation