摘要
针对一种设计飞行马赫数范围为2．25～4．0的定几何混压式二元超声速进气道由于反压引起的不起动开展了再起动特性风洞实验研究．根据实验结果和二维非定常数值仿真结果分析表明：在Ma=2．51和3．01下进气道性能在进锥／退锥实验中规律一致；按照Ma=2．25的起动面积收缩比确定的喉道面积，使进气道在来流Ma≥2．51时具有自起动能力；而在稳定亚临界状态下具有高的总压恢复系数及形成类似于外压式的气动通道是进气道无回路迟滞现象的主要原因．
An experimental study was conducted to investigate the restart performance of a fixed-geometry,mixed-compression,two-dimensional supersonic inlet under unstart condition due to raising backpressure,with a designed flight Mach number from 2.25 to 4.0. The test results and two-dimensional unsteady simulation results show that, the inlet performance is consistent in the inlet wall and exit section tests at Mach number of 2.51 and 3.01; the throat area is determined according to the start area shrinkage ratio at Mach= 2.25, so that the inlet enables self-start at Ma = 2.5 and above. The phenomenon of no hysteresis under stable subcritical condition is because of a high total pressure recovery and a flow pattern of inlet similar to external compression inlet.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2008年第2期389-395,共7页
Journal of Aerospace Power
