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针对可利用部分冲压、带前输出轴直升机进气道结构特点 ,实验研究了在侧滑角从 0～ 1 35°状态下的直升机进气道流场特性 ,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。研究表明 ,该类进气道在各种侧滑状态下总压恢复系数较高。当侧滑角大于 90°时总压恢复系数随着来流速度的增加而减小 ;进气道内气流分离的区域和出口截面流场畸变指数与侧滑角和来流速度的大小有关。其中在侧滑角小于 90°时 ,进气道出口截面流场品质较好。当侧滑角大于90°时 ,随着来流速度或侧滑角的增加出口流场迅速恶化
In view of the structural characteristics of partially-ram-equipped helicopter inlet with front-output shaft, the characteristics of the helicopter inlet flow field with side-slip angle from 0 to 1 35 ° are studied. Airway exit section flow field distortion index, total pressure recovery coefficient and other inlet performance parameters. The research shows that the total pressure recovery coefficient of this kind of inlet is higher under all kinds of skidding conditions. When the side slip angle is more than 90 °, the total pressure recovery coefficient decreases with the increase of the inflow velocity. The flow field distortion index in the region where the air flow separates and at the exit section is related to the side slip angle and the inflow velocity. Among them, when the side slip angle is less than 90 °, the flow field at the inlet outlet section is of better quality. When the side slip angle is more than 90 °, the outlet flow field deteriorates rapidly with the increase of the flow rate or the side slip angle