摘要
对一种腹下后置大偏距S弯进气道进行高速风洞试验研究,得到了该进气道的工作特性:(1)随着流量系数的增加,进气道出口总压恢复系数略有下降,稳态周向畸变指数、紊流度和综合畸变指数均上升;当流量系数较大或较小时,进气道出口气流总压脉动均存在局部峰值。(2)在试验研究范围内,来流马赫数和侧滑角的变化对进气道性能影响不大;随着迎角的增大,总压恢复系数有所上升,畸变指数有所下降。(3)进/发匹配点处,进气道出口气流总压脉动功率谱密度分布呈现白噪声特征,对进气道/发动机匹配工作是有利的。
Experiments of aft mounting ventral S-shaped inlet with high offset is conducted in a high speed wind tunnel.Results show that：（1）When the mass flow ratio of the inlet increases,the total pressure recovery decreases slightly,and the circular steady total pressure distortion,turbulence intensity and synthesis distortion all increase.When the deviation of the mass flow ratio from designed point is large enough,the peek value of power spectrum of the dynamic total pressure signals will appear.（2） According to the present results,the free stream Mach number and the yaw have little effect on the inlet performance,and the positive incidence is favorable to the inlet performance.（3） At the point where the inlet is compared with engine,the power spectrum of the dynamic total pressure signals at the engine face generally shows the characteristics of white noise,which is beneficial to inlet-engine compatibility.
出处
《南京航空航天大学学报》
CAS
CSCD
北大核心
2012年第1期1-7,共7页
Journal of Nanjing University of Aeronautics & Astronautics
关键词
航空航天推进系统
腹下S弯进气道
总压恢复系数
畸变指数
功率谱
aerospace propulsion system
ventral S-shaped inlet
total pressure recovery
distortion coefficient
power spectrum
