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.
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.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2011年第9期2133-2140,共8页
Journal of Aerospace Power
关键词
埋入式进气道道
大偏距
总压恢复系数
畸变指数
功率谱
submerged inlet
high offset
total pressure recovery
distortion coefficient
power spectrum
