| 一种可利用部分冲压的直升机进气道流场特性实验研究(英文) |
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| 引用本文： | 韩东,郭荣伟,万大伟,李良辉,孙姝. 一种可利用部分冲压的直升机进气道流场特性实验研究(英文)[J]. 南京航空航天大学学报(英文版), 2001, 18(2) |
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| 作者姓名： | 韩东 郭荣伟 万大伟 李良辉 孙姝 |
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| 作者单位： | 南京航空航天大学能源与动力学院, |
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| 摘 要： | 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
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| 关 键 词： | 直升机进气道 侧滑 总压恢复 畸变 |
CHARACTERISTICS OF FLOW IN A PARTIALLY DYNAMIC HELICOPTER INLET |
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| Han Dong,Guo Rongwei,Wan Dawei,Li Lianghui,SUN Shu. CHARACTERISTICS OF FLOW IN A PARTIALLY DYNAMIC HELICOPTER INLET[J]. Transactions of Nanjing University of Aeronautics & Astronautics, 2001, 18(2) |
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| Authors: | Han Dong Guo Rongwei Wan Dawei Li Lianghui SUN Shu |
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| Affiliation: | Han Dong Guo Rongwei Wan Dawei Li Lianghui Sun Shu College of Energy and Power Engineering,NUAA29 Yudao Street,Nanjing 210016,P.R.China |
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| Abstract: | An experimental study of the flow in a helicopter inlet with front output shaft and partial flow dynamic head is conducted in low speed wind tunnel. The flow characters of the inlet in the range of the yaw angle from 0～135°are presented in this paper. The static pressure distributions along the duct, distortions of the flow field at the outlet section and total pressure recovery coefficients are measured and analyzed. The results show that this type of inlet has high total pressure recovery coefficients at a wide range of yaw angle. The regions of local flow separation and distortion are closely related to the yaw angle.Its also found that the outlet section has the best characteristics at sideslip, and sharply deteriorated characteristics at the yawed flight with a yaw angle of more than 90° |
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| Keywords: | helicopter inlet yawed flight total pressure recovery distortion |
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