马赫数4一级下颔式混压进气道试验

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. 

Experiment of a Ma4 chin inlet with mixed-compression

Experiment of a Ma4 chin inlet with mixed-compression had been done,the pneumatic performance of the inlet was obtained.The results showed that: (1) When Ma=3.5,angle of attack and angle of yaw are both 0 degree,the total pressure recovery coefficient increased at first and then decreased with the increasing of back-pressure,the total pressure recovery coefficient got its maximum at the critical state. (2) Under the critical states of angle of attack and angle of yaw are both 0 degree.The total pressure recovery of inlet decreased linearly with the increasing of flight mach number. (3) The inlet performance declined under pitch or yaw conditions. (4) The inlet has restarting character in the unstart process caused by back-pressure,phenomenon of hysteresis is not obtained in the loop from start to restart induced by the back pressure during the mass adjustor moving forward/backward process(AFBP).