有翼航天飞行器高速动态气动特性试验研究  

The experimental research of winged vehicle for dynamic aerodynamic characteristics at high speeds

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》2004年第3期13-18,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：在CARDC0.6m×0.6m高速风洞中进行了航天飞机类模型的动态失速试验。在M数为0.4～1.2,迎角为0°～75°范围测量了模型的动态气动特性,研究了各种运动参数对动态气动特性的影响。结果表明,在试验范围内,俯仰振荡引起了不同程度的气动迟滞现象,各运动参数对模型的动态气动特性都有重要影响,仅在迎角约为20°～40°时,非定常法向力增量存在,相应的非定常效应较明显。The dynamic stall test of the space shuttle-like model was conducted in CARDC 0.6m×0.6m high speed wind tunnel.Dynamic aerodynamic characteristics of the model were measured over the Mach numbers range from 0.4 to 1.2 and the range of angles of attack from 0°to 75°,and effects of motion parameters on aerodynamic characteristics were investigated. The results show that pitching oscillations result in aerodynamic hysteresis, the parameters of motion have important effects on dynamic aerodynamic characteristics of the model in the test range. There are the increments of unsteady normal force, and relevant unsteady effects are obvious only about at the angles of attack from 20°to 40°.

关 键 词：有翼航天飞行器 动态试验 动态失速 非定常空气动力学 大迎角空气动力学 

分 类 号：V475[航空宇航科学与技术—飞行器设计]