摘要
本文详细地叙述了实验马赫数为０．８和１．５，攻角直到２５°时，尖顶襟翼／涡襟翼干扰对三角翼背风面流动的影响。用蒸汽屏和纹影技术，显示出涡系干扰的流动图像，测量了尖顶襟翼在不同偏角下，三角翼上表面展向压力分布。数据分析表明：偏角、攻角和马赫数对背风面流动特性有重要的影响。指出涡系干扰仅在负偏角下可增大机翼升阻比。
This paper describes in detail the effect of apex-flap/vortex-flap interaction on lee-surface flow oyer delta wing at M=0. 8and 1.5 for angle of attack up to 25°.The flow patterns of interaction of separated vortices are shown by using laser vapor-screen and schlieren techniques. The spanwise pressure distributions on upper surface of wing are presented at various deflections of the apex-flap. Analysis of data shows an important influence of deflection, angle of attack and Mach number on the lee-surface flow characteristics. The experiment indicated that vortices interaction can increase the lift-drag ratio of the wing only at negative deflection.
出处
《空气动力学学报》
CSCD
北大核心
1996年第2期223-229,共7页
Acta Aerodynamica Sinica
基金
国家自然科学基金
关键词
涡襟翼
流动显示
压力测量
分离流
vortex flap, flow visualization,pressure measurement,separated flow.
