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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。
The effects of high angle of attack (α = 0 ° ~ 45 °) and side slip angle (β = -1 5 ° ~ 1 5 °) on the aerodynamic performance of Caret inlet were studied under low flow conditions. The characteristics of inlet port performance parameters with side slip angles at various angles of attack and the map of the distribution of the total pressure recovery coefficient at the outlet of the inlet are given. The relationship between the distribution of the outlet pressure profile and the inlet flow is analyzed relationship. The experimental results show that with the increase of angle of attack (α increased from 0 ° to 45 °) at low flow rate (Ma≈0.1), the total inlet pressure recovery coefficient decreases slightly, and the total pressure distortion index Almost unchanged, which is conducive to the aircraft’s high angle of attack maneuvering.