带前体压缩的前掠侧压式进气道实验及数值研究

Experimental and numerical investigation of a forward sweep sidewall compression scramjet inlet with forebody compression

关键词:  超燃冲压发动机  前掠侧压式进气道  风洞实验  数值仿真

Key words:  Scramjet  Forward-sweep sidewall compression inlet  Wind tunnel experimentation  Numerical simulation

摘要:

为提高侧压式进气道流量系数,设计了一种前机身顶压与侧压相结合的前掠侧压式进气道,在马赫5.3小高超风洞中完成吹风实验,并用FLUENT软件对进气道流场进行了数值模拟,分析了主要流动特征,获得了进气道基本性能。实验结果表明,马赫5.3设计状态下,这种前掠侧压式进气道的流量系数可以达到0.85以上,比一般后掠进气道提高20%左右。通过数值及实验研究发现,进气道下游隔离段内由于上下壁面的巨大压差导致顶板对称面两侧出现对涡,涡面将隔离段内的流动分为高速高能区与低速低能区两种流动。

Abstract:

A generic forward sweep sidewall compression scramjet inlet with forebody compression was designed to improve the performance of mass capture.Experiment was conducted in NUAA 100mm×100mm Mach 5.3 wind tunnel. The flow field was numerically simulated by means of FLUENT software.Based on the numerical and experimental result,typical characteristics of the flow field were identified,and the main performance parameters were obtained.Experimental results indicate at Mach 5.3 design point,the forward sweep sidewall compression inlet has a mass capture ratio of above 0.85,which is about 20% higher than that of the conventional backward sweep inlet.Combined with the numerical result,Pitot-pressure distribution at the exit of the isolator shows a pair of vortexes occuring at the bottom of the isolator because of the high pressure difference between topwall and bottomwall,which separates the flow of the isolator into two regions.One region has high speed and high total pressure recovery and the other has low speed and low total pressure recovery.