Busemann进气道风洞实验及数值研究  

Experimental investigation and numerical simulation of hypersonic Busemann inlet

作　　者：孙波[1] 张堃元[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《推进技术》2006年第1期58-60,96,共4页Journal of Propulsion Technology

摘　　要：为了获得Busem ann进气道的流场特性和总体性能,利用内锥形流场生成了设计马赫数为5.3,收缩比为8的具有乘波构形的Busem ann进气道,对该进气道进行了数值模拟和Ma为5.3的吹风实验,实验测量了进气道内的沿程静压分布和出口截面的皮托压力,分析了进气道的压缩特性和乘波特性,获得了进气道的基本性能参数。实验结果表明:该进气道流量系数为0.58,出口马赫数1.4,总压恢复0.217,增压比37.6。A partial Busemann inlet was designed for Mach 5.3 flight and has a contraction ratio of 8 and was tested in the wind tunnel at Mach 5.3, which is applied to the inward turning air-breather. Distributions of the static pressure along the centerlines of the top wall, sidewall and cowl bottom wall, and Pitot-pressure of the isolator exit plane were experimentally obtained. Static pressure distributions were compared with the numerical results simulated by Fluent software and show good agreement. The characteristics of inlet on compression and waveride were analyzed. Experimental results indicate the inlet has a better performance with a mass capture ratio 0. 58, averaged Mach number 1.4, total pressure recovery O. 217, and compression pressure ratio 37.6 at the isolator exit plane.

关 键 词：超音速冲压喷气发动机 高超声速进气道 BUSEMANN进气道 进气道设计 

分 类 号：V235.213[航空宇航科学与技术—航空宇航推进理论与工程]