Wind Tunnel Test and Numerical Study on Civil Aircraft Inlet Performance under Low Speed and High Angle of Attack Condition

被引：0

作者：

Wang L. ^{[1
]}

Liu K.-L. ^{[1
]}

Chen Y. ^{[1
]}

Si J.-T. ^{[1
]}

Zhou S.-R. ^{[1
]}

Shao Q.-L. ^{[1
]}

机构：

[1] Shanghai Aircraft Design and Research Institute, Commercial Aircraft Corporation of China Ltd, Shanghai

来源：

Tuijin Jishu/Journal of Propulsion Technology | 2021年 / 42卷 / 06期

关键词：

Flow separation; Inlet; Nacelle; Numerical simulation; Stall; Total pressure distortion; Wind tunnel test;

D O I：

10.13675/j.cnki.tjjs.200262

中图分类号：

学科分类号：

摘要：

In order to investigate the flow character and performance of civil aircraft inlet under low speed and high angle of attack condition, wind tunnel test and numerical simulation are conducted for an inlet with design Mach number of 0.785, under the condition of coming flow Mach number 0.2, angle of attack from 0°~25°, and mass flow ratio from 0.29~2.07. The results show that, under take off condition, the inlet could work under angle of attack up to 25°.Under take off condition with one engine inoperative, the inlet external flow separation may occur at angle of attack 13°~16°.Under high angle of attack condition without flow separation, mass flow ratio has limited influence on the inlet distortion. Based on the results, the inlet flow character under low speed and high angle of attack condition, and its variation with angle of attack or mass flow ratio is analyzed. Comparison between numerical simulation and wind tunnel test results show that, the two could coincide with each other when no flow separation occurred, however, the difference of external flow separation angle could be up to 3°, suggesting wind tunnel test is still necessary to validate the inlet performance. © 2021, Editorial Department of Journal of Propulsion Technology. All right reserved.

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页码：1235 / 1244

页数：9

共 29 条

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