低速来流大攻角侧滑角状态下尖脊进气道气动特性试验研究

在低速来流状态下试验研究了大攻角 (α=0°～ 4 5°)和侧滑角 (β=-1 5°～ 1 5°)对 Caret进气道气动性能的影响。给出了在各攻角下进气道性能参数随侧滑角变化的特点及典型状态下进气道出口总压恢复系数分布图谱 ,分析了出口总压分布图谱与进气口流动之间的关系。试验表明 :在低速来流状态 (Ma≈ 0 .1 )下 ,随着攻角的增加 (α从 0°增加到 4 5°) ,进气道总压恢复系数下降较小 ,总压畸变指数几乎不变 ,这有利于飞机的大攻角机动飞行。

Experimental Investigation on Gas-Dynamic Performance of Caret Inlet under Condition of Large Attack Angles and Yaw Angles

An experimental investigation has been carried out.The influencesof attack angle （α=0°～45°） and yaw angle （β=-15°～+15°） on caret inlet gas-dynamic performance were investigated experimentally.The variation of the inlet performance parameters with the attack angles,as well as total pressure contour plots of inlet/exit at typical states,have been presented,and the relationship between flow characteristics of the inlet and its exit total pressure contour plots has also been analyzed.It is shown that,in the condition of low speed incoming flow (Ma≈0.1),the inlet total pressure recovery coefficient decreases slowly with the increase of attack angle （α=0°～45°）,and the total pressure distortion is nearly unchanging.As a result,caret inlet is favorable to maneuver flight at large attack angle.With zero attack angle and at same exit Mach number,the yaw angle has a great influence on position of inlet/exit higher and lower total pressure domains,i.e.the whole exit flow field rotates clock-wise as the yaw angle increases （β=-15°～+15°）.However,the influence of the yaw angle becomes weaker with the increase of attack angle.