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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。
Wind tunnel tests are usually used to reduce the total operating pressure to expand the wind tunnel Reynolds number simulation of the lower boundary. Compared with the normal pressure test, under the condition of low Reynolds number, there is a significant change in the flow field in the wind tunnel, and whether the quality of the flow field in the wind tunnel meets the index requirements will directly affect the accuracy of wind tunnel test data. In order to study the effect of low Reynolds number effect on the performance of 0.6 m continuous transonic wind tunnel (including axial compressor performance, total pressure and Mach number control accuracy, flow field uniformity) A lot of related experiments have been carried out in the wind tunnel. Based on the collation and analysis of the test results, this paper gives the influence of Re on the performance of the wind tunnel. The results show that: (1) Re has a significant effect on compressor performance, total pressure control accuracy, Mach number control accuracy and flow field uniformity. When Rec <5 × 10 ~ 5 (c = 0.1A ~ ), Reynolds number effect is obvious, and Re smaller, the greater the impact. (2) The 0.6m continuous transonic wind tunnel can accurately and accurately reflect the influence law of Re on the flow field performance and force test data of wind tunnel, and is an ideal ground for research on the performance of low altitude Reynolds number aircraft, airfoil and engine Simulation test platform.