摘要
应用骑波机理论设计了一个设计Ｍａ数为２的“Ｃａｒｅｔ”进气口，并试验研究带有该进气口的矩形大Ｓ弯扩压器在地面起飞状态下的流动特性。通过壁面流谱观察，有关截面的总压恢复系数分布图和速度矢量图等分析了进气口和Ｓ弯扩压器流动特性。并与带有常规进气口的该大Ｓ弯扩压器性能进行对比。试验结果表明在地面起飞状态下及相同扩压器出口平均Ｍａ数下，带有“Ｃａｒｅｔ”进气口的大Ｓ弯扩压器出口总压恢复系数略高于带有常规进气口的大Ｓ弯扩压器的值。
A 'caret' inlet was designed for Mach number 2 0 according to theory of waverider.The experimental investigation on flow characteristics of a large S-shaped diffuser with such an inlet has been carried out.The flow characteristics of the inlet and the S-shaped diffuser have been analysed by means of flow visulization on the walls,measurements of total pressure recovery distribution and velocity vector plots in the sections concerned.The performance of this large S-shaped diffuser was compared with that of the same diffuser but with conventional inlet.It is shown that,under takeoff condition and at the same Ma 2 of the diffusers,the total pressure recovery of the former is a little higher but the circumferential total pressure distortion index △ σ o and DC60 of the former are larger than that of the latter.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
1996年第4期385-388,共4页
Journal of Aerospace Power
关键词
进气道
扩压器
总压力
分离流动
Engine inlets Diffusers Total pressure Separated flow
