压缩性对大振幅俯仰振荡三角翼动态特性影响的试验研究  

The experimental research of compressibility effects on dynamic characteristics of delta wings at pitching oscillation of large amplitude

作　　者：郑世华[1] 徐永长[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《流体力学实验与测量》2002年第4期75-80,共6页Experiments and Measurements in Fluid Mechanics

基　　金：国家高技术航天领域资助项目(863-2-6-5)

摘　　要：对飞行器在高速大迎角时的动态气动特性的研究是很重要的。在CARDC进行了高速风洞动态失速试验技术研究,使用专用的动态失速机构,以60°、70°和76°三角翼为模型,在M=0.4～1.0范围内,在不同振幅、不同频率情况下进行了风洞试验,分别测量了各三角翼的动态气动载荷,研究了在大振幅俯仰振荡时各三角翼的动态气动特性,重点研究了压缩性对三角翼动态特性的影响。结果表明随着M数的增加,上述三种三角翼的非定常效应减弱。The study of dynamic characteristics of a vehicle at high speeds and high angle of attack is quite important. The testing technique research of dynamic stall was conducted in a high speed wind tunnel of CARDC at different amplitudes and frequencies, test Mach numbers ranged from 0.4 to 1.0. 60°, 70°and 76°delta wing models and specialized dynamic stall mechanism were used. The unsteady aerodynamic force and moment of delta wings were measured. The investigation was focused on compressibility effects on dynamic characteristics of delta wings. The results show that the unsteady effects is weakened as Mach number increases.

关 键 词：风洞试验 俯仰特性 压缩性效应 动态试验 飞行器 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]