扰流板进气总压畸变试验

在吊舱进气道进口安装扰流板进行试验，研究扰流板进气畸变的影响因素及总压畸变特征。试验得到了进气道出口若干马赫数下进气总压畸变的定量数据，研究了进气道出口压力分布和畸变指数随飞行马赫数、扰流板堵塞比、进气道出口马赫数的变化关系。试验结果表明：进气道出口对应点总压恢复系数随扰流板堵塞比和进气道出口马赫数的减小而增大，几乎不随飞行马赫数发生变化；受扰流板、飞行侧滑角以及发动机低压转子转向影响，进气道出口局部区域存在高压区，高压区域的大小和位置随飞行马赫数、扰流板堵塞比、进气道出口马赫数的变化而变化；各总压畸变指数随扰流板堵塞比和进气道出口马赫数增大而增大，飞行马赫数对畸变指数影响很小。同时，数值计算了不同飞行马赫数下进气道出口总压畸变特征及周向稳态畸变指数，与试验结果结论一致，验证了试验结果的可靠性，也证明了数值计算在总压畸变研究中的有效性。研究工作为进一步的空中逼喘试验奠定了基础。

Test Investigation of Disturbed Board Total Pressure Distortion

Characteristics and influence factors of total pressure distortion are studied based on tests conducted on a disturbed board installed in the nacelle inlet.Values are obtained about the total pressure distortion at several inlet exit Mach numbers,and the relationships are discussed between the inlet exit total pressure distribution and distortion indexes and the flight Mach number,the disturbed board blockage ratio and the inlet exit Mach number.The test results show that the total pressure recovery of the ...