论文部分内容阅读
进气道是飞行器动力装置的重要组成部分,准确测量进气道流量系数是进气道风洞试验的重要内容。对来流马赫数Ma=4.5,5.0和6.0状态下皮托管进气道开展流量系数测量研究,通过对比理论值和实测值,获取各状态流量系数修正系数。试验结果表明,随着来流马赫数增加,进气道流量系数与理论值偏差较明显,并逐渐增大。超声速风洞试验通常认为测量截面总温与来流总温相等,通过对测量截面总温与来流总温偏差以及测量截面流场畸变情况的分析,判断测量偏差主要是由测量截面总温等于来流总温的假设导致的。在高超声速风洞试验中,由于模型壁面热交换的存在,测量截面总温低于来流总温,进气道流量系数测量时需要进行总温修正,以提高流量测量精度。
Intake air intake is an important part of aircraft power plant. Accurate measurement of intake air flow coefficient is an important part of intake tunnel test. The flow coefficient of Pitot tube inlet was measured under Ma = 4.5, 5.0 and 6.0. The correction coefficient of each state flow coefficient was obtained by comparing the theoretical value with the measured value. The experimental results show that with the increase of Mach number, the deviation of inlet flow coefficient from the theoretical value is obvious and gradually increases. The supersonic wind tunnel test usually considers the total cross-sectional temperature to be equal to the total temperature of the incoming flow. By analyzing the total cross-sectional temperature and the total temperature deviation of the incoming flow and the distortion of the cross-section flow field, the measurement deviation is mainly determined by measuring the total cross-section temperature equal to The assumption of the total temperature of the influx. In the hypersonic wind tunnel test, the total temperature of the measured section is lower than the total temperature of the incoming flow because of the heat exchange on the wall of the model. The total temperature correction is needed when measuring the inlet flow coefficient to improve the measurement accuracy of the flow.