空气动力学学报2016，Vol.34Issue(3)：398-403,6.DOI:10.7638/kqdlxxb-2015.0152
高超声速风洞变雷诺数试验技术研究
Research on the test technique of Reynolds number variety in a hypersonic wind tunnel
谢飞 1郭雷涛 1朱涛 1邹琼芬1
作者信息
- 1. 中国空气动力研究与发展中心 超高速空气动力研究所,四川 绵阳 621000
- 折叠
摘要
Abstract
Research on the test technique of Reynolds number variety is conducted in theΦ1 m Hypersonic Wind Tunnel in CARDC to fulfill the needs of Reynolds numbers effect simulations for hypersonic vehicles.Because the run-mode of theΦ1 m Hypersonic Wind Tunnel is high-pressure and vacuum-pumping,it owns a wide range of operational condition,the test Reynolds number can be changed by the way of stagnation pressure changing.The test technique of Reynolds number change consists of two types:single-point Reynolds number change method and continuous Reynolds number change method.The single-point Reynolds number change method keeps the stagnation pressures a fixed value to obtain aerodynamic coefficients with different attitude angles.The continuous Reynolds number change method keeps test model with a fixed attitude and continuously change stagnation pressure from high to low to obtain aerodynamic coefficients with different Reynolds number.The run-modes of wind tunnel,test measurement and data process method are presented in detail,and the validation tests of a lifting-body aircraft and a missile models have been presented. Combining continuous Reynolds number change method with single-point Reynolds number change method,we can completely and accurately obtain the aerodynamic characteristics of hypersonic vehicle with Reynolds number changing. The test results show the application prospect of this test technique.关键词
高超声速风洞/雷诺数/气动力/试验技术Key words
hypersonic wind tunnel/Reynolds number/aerodynamics/test technology分类
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谢飞,郭雷涛,朱涛,邹琼芬..高超声速风洞变雷诺数试验技术研究[J].空气动力学学报,2016,34(3):398-403,6.
