摘要
风洞试验中通常采用降低运行总压的方法来扩大风洞雷诺数模拟的下边界。同常压试验相比,在低雷诺数条件下,风洞流场是否存在明显变化,风洞流场品质是否满足指标要求,直接影响风洞试验数据的精准度。为了研究低雷诺数效应对0.6m连续式跨声速风洞性能(包括轴流式压缩机性能、总压及马赫数控制精度、流场均匀性)的影响,调试人员在0.6m连续式跨声速风洞中开展了大量相关试验,本文在对试验结果进行整理、分析的基础上,给出了Re对风洞性能的影响。结果表明:(1)Re对压缩机性能、总压控制精度、马赫数控制精度、流场均匀性都有明显影响,当Rec<5×10~5(c=0.1A^(1/2))时,雷诺数效应明显,且Re越小,影响越大。(2)0.6m连续式跨声速风洞能够真实、准确反映Re对风洞流场性能和测力试验数据的影响规律,是开展高空低雷诺数飞行器、翼型、发动机等性能研究的理想地面模拟试验平台。
In the wind tunnel tests, the method of decreasing stagnation pressure is usually adopted to expand the simulation scope of Reynolds number. Compared with the normal pressure test, in the low Reynolds number situation, the accuracy of the test data is directly affected by whether or not the change of the flow field is obviously and whether or not the quality of the flow field satisfies the index. In order to study the influence of Reynolds number on the 0.6m continuous wind tunnel performance, the relevant tests were carried out in the 0.6m continuous wind tunnel. Based on arrangement and analysis of the tests data, the results were given. It shows that： （1） The Reynolds number has obvious effect on the performance of the compressor, stagnation pressure control precision, Mach number control precision, the flow uniformity etc. When Rec〈10^5（c=0.1√A）, A is the cross-sectional area of the test section）, the effect of Reynolds number on the performance of wind tunnel is obvious. The smaller the Reynolds number is, the greater the effect is. （2） The 0.6m continuous wind tunnel can accuratly manifest the influence law of the effects of Reynolds number on the flow field performance of the wind tunnel and the force test data. Therefore, it is a good test platform for the capability research on aircraft, airfoil, engine, etc. , at low Reynolds number.
出处
《实验流体力学》
CAS
CSCD
北大核心
2017年第1期87-92,99,共7页
Journal of Experiments in Fluid Mechanics
关键词
雷诺数
压缩机
连续式风洞
流场性能
Reynolds number
compressor
continuous wind tunnel
flow field performance
