超音速轴对称进气道唇口分离流吹除及其动态畸变源相干分析

The Blowing-off of the Lip Separation of an Axisymmetric Supersonic Inlet and the Analysis of the Coherence of Dynamic Distortion of the Inlet

本文研究了马赫数M_∞=2.0一级的双锥轴对称超音速进气道在起飞状态下,自大气引入射流,吹除唇口内侧壁面强烈的气流分离和倒流对进气道沿程静压脉动以及对其出口脉动总压的影响;并对进气道出口的动态畸变源作了相干分析。

It is found in the experiments that the blowing-off of the lip separation of the inlet reduces obviously the turbulences at the inlet exit, and apparently the intensity of pressure fluctuation caused by the shock boundary interaction downstream of the throat. The coherence between the pressure in the interaction region and total pressure at the exit is also reduced.The coherence between the pressure in the lip separation region and total pressure at the exit is 0.32. If, in addition, there is a strong shock downstream of the throat the above mentioned coherence is reduced to 0.06.