超声速细长梯形翼背风面流型  

Types of Flow over Leeside of a Slender Tapered Wing at Supersonic Speeds

作　　者：洪金森[1] 

机构地区：[1]北京空气动力研究所,北京100074

出　　处：《空气动力学学报》1997年第1期47-53,共7页Acta Aerodynamica Sinica

摘　　要：给出了前缘后掠角65°，双弧形剖面的细长梯形翼背风面流动显示结果。实验马赫数为1．10、1．53、2．53、3．01和4．01，攻角范围5°～25°。借助于蒸汽屏、纹影和油流技术拍摄了脱体和表面流型照片。蒸汽屏显示表明：在机翼背风面三角形区域的脱体流型可在垂直于前缘的法向攻角和法向马赫数构成的坐标平面上，区分出七种不同的流型；在切尖区域，有侧缘分离涡形成，后缘拖出尾涡。从摄取的纹影照片与横截面上的蒸汽屏照片一起，可获得机翼弓形激波位置随马赫数变化，以及激波－诱导分离线位置随马赫数和攻角变化曲线。在机翼上表面通过油流显示出主再附线、二次分离线、二次再附线和侧缘涡区。显示出的流型与其它有关实验和数值计算结果比较，符合得很好。This paper describes a flow visualization experiment over leeside of a slender tapered wing with a leading edge sweep back angle of 65°and a bicovex section. By using of 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°Photos of flow off-body and on Iee-surface have been taken. The vaporscreen photos show seven distinet types of flow developed over the delta region of the wing. These types of flow displayed in a plane of Mech number and angle of attack normal to the leading-edge. In the region of side-edge, there are side voritices formed, and in the region of trailing edlge trailing vortices shed. The variations of both the shock positions at different Mach numbers and the positions of separating lines induced by shock wave with Mach number and angles of attack have been obtained based upon the schlieren plus the vaper-screen photos in the sections.The oil-flow visualization shows clearly primary reattachment, secondary separation. secondary rettachment lines, and side edge vortices on the lee-surface. The results of this test are in good agreement with experiments and numerical simulation results of the others.

关 键 词：流动显示 旋涡 激波-诱导分离 机翼气动力学 

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] V211.74