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本文针对带有前输出轴直升机进气道结构特点 ,以实验的方法 ,在直升机飞行包线范围内 ,着重研究在侧滑角从 0°到 1 3 5°状态下的直升机进气道流场特性 ,测量分析了沿程静压分布、进气道出口截面流场畸变指数、总压恢复系数等进气道性能参数。研究结果表明 ,这类进气道在各种侧滑状态下总压恢复系数较高 ,且与侧滑角的关系不大。但是进气道内气流分离的区域和出口截面流场畸变指数却与侧滑角的大小密切相关。其中在侧滑角为 90°时 ,进气道出口截面流场品质最佳 ,而当侧滑角大于 90°时 ,出口流场迅速恶化
In this paper, the helicopter inlet flow field with front-output shaft is studied experimentally in the flight envelope of helicopter, focusing on the helicopter inlet flow field with side-slip angle from 0 ° to 135 ° Characteristics, measured and analyzed along the static pressure distribution, inlet cross-section flow field distortion index, the total pressure recovery coefficient of inlet performance parameters. The results show that the total pressure recovery coefficient of such inlet in all sideslip conditions is high, and has little to do with the side slip angle. However, the flow field distortions in the region where the airflow is separated and at the exit cross section are closely related to the size of the side slip angle. Among them, when the side slip angle is 90 °, the flow field at the inlet cross-section is of the best quality. When the side slip angle is more than 90 °, the outlet flow field rapidly deteriorates