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对一种Ma=4一级下颔式混压进气道进行了试验,得到了该类进气道的气动特性,结果表明:①在Ma=3.5,攻角和偏航角为零时,随着出口反压的增加,进气道总压恢复系数先升高后降低,临界状态下进气道总压恢复系数最高;②攻角和偏航角为零时临界状态时,随着来流马赫数的增加,进气道的总压恢复系数呈线性下降趋势;③有攻角或偏航角的状态下进气道的总压恢复系数有所下降;④进气道在由反压引起的不起动过程中具有再起动特性,再起动过程中无迟滞廻路现象.
The experimental results show that: (1) when Ma = 3.5 and the angle of attack and yaw are zero, the aerodynamic characteristics of this type of inlet are obtained. With the increase of outlet backpressure, the total inlet pressure recovery coefficient firstly increases and then decreases, and the total inlet pressure recovery coefficient is the highest in the critical condition. When the angle of attack and the yaw angle are zero, The increase of flow Mach number, the total pressure recovery coefficient of inlet decreases linearly; ③ the total pressure recovery coefficient of inlet decreases with the angle of attack or yaw angle; Caused by the start-up process has a restart feature, no hysteresis during the restart of the phenomenon of 迴 Road.