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根据激波和膨胀波理论,设计了Ma=5.3等压力梯度曲面压缩系统。在Ma=3.85和Ma=5.3的小高超风洞完成均匀来流试验,并利用风洞壁面自然发展的附面层进行非均匀来流等压力梯度曲面压缩系统性能试验。试验发现:均匀来流下,试验模型壁面压力均按照等压力梯度规律分布,但来流马赫数Ma=5.3时出口流场均匀性较差;非均匀来流下,大量的附面层吸入不仅影响壁面压力不再呈等压力梯度分布,而且对出口流场均匀性影响也极大。
According to shock wave and expansion wave theory, a pressure gradient surface compression system with Ma = 5.3 is designed. The uniform flow test was carried out in the small ultra-high wind tunnel with Ma = 3.85 and Ma = 5.3. The performance of the pressure gradient surface compression system such as non-uniform flow was tested by using the naturally occurring surfacing of the wind tunnel wall. The experimental results show that the wall pressure of the experimental model is distributed according to the regularity of equal pressure gradient when the flow rate is uniform, but the uniformity of the outlet flow field is poor when the flow Mach number is 5.3. Inhomogeneous flow, a large number of in-layer suction not only affects the wall The pressure is no longer equal pressure gradient distribution, but also has a great influence on the uniformity of the outlet flow field.