一种大偏距埋入式进气道气动特性试验

翁小侪; 谢文忠; 郭荣伟

一种大偏距埋入式进气道气动特性试验

1.
南京航空航天大学能源与动力学院,南京 210016
2.
中国人民解放军 94710部队,江苏无锡 214141

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出版历程
- 收稿日期: 2010-10-11
- 修回日期: 2011-03-15
- 刊出日期: 2011-09-28

Experimental investigation on flow characteristics of a submerged inlet with high offset

1.
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
Unit 94710, The Chinese People's Liberation Army, Wuxi Jiangsu 214141, China

摘要

摘要: 对一种大偏距埋入式进气道进行了高速风洞试验研究,得到了该进气道的气动特性,结果表明:①巡航状态时,出口马赫数的变化对进气道性能影响不大,进气道具有较高的巡航性能.②在试验研究的范围内,随飞行马赫数的增加,进气道性能有所下降;攻角的增加对进气道性能有所改善,侧滑角的变化对进气道性能影响不大.③进/发匹配点时,进气道通道内气流脉动功率谱密度分布呈现白噪声特征,在大攻角或偏航条件下进气道气流脉动功率谱密度有明显的峰值.
- 埋入式进气道道 /
- 大偏距 /
- 总压恢复系数 /
- 畸变指数 /
- 功率谱
Abstract: Experiments of a submerged inlet with high offset were made and described in this paper.The study was carried out in a high speed wind tunnel.The results show that:(1) Under cruising condition,the Mach number at the exit has little effect on the inlet performance.(2) According to the experimental results,when the free stream Mach number increases,the total pressure recovery decreases and the synthesis distortion rises.The rising incidence is favorable to the inlet performance,but on which the yaw has little influence.(3) At the matching point of the inlet with engine,the power spectrum of the dynamic pressure signals in the duct generally presents the characteristics of white noise;however at high incidence or yaw the power spectrum has some narrow band peak value.
- submerged inlet /
- high offset /
- total pressure recovery /
- distortion coefficient /
- power spectrum

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参考文献(17)

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