自由射流中飞机进气道前方亚声速流场数值仿真研究  

Numerical calculation of subsonic flow field in front of aircraft inlet duct in free jet

作　　者：王键灵 徐让书[1,2] 侯亚军[1] 王娟娟[3] 

机构地区：[1]沈阳航空航天大学航空航天工程学部,沈阳110136 [2]沈阳航空航天大学辽宁省航空推进系统先进测试技术重点实验室,沈阳110136 [3]中国航空工业集团公司中国航空工业研究院 航空发动机高空模拟航空科技重点实验室,四川江油621703

出　　处：《沈阳航空航天大学学报》2014年第5期39-43,共5页Journal of Shenyang Aerospace University

摘　　要：为了预测航空发动机高空模拟自由射流试验中飞机进气道-发动机组合体前方的亚声速流场特性,优化试验舱的气动设计,采用CFD方法在亚声速自由射流和真实大气飞行条件下对某战斗机进气道的外流场进行数值模拟。分析了进气道对前方气流压缩作用与飞行马赫数关系,对比和分析了分别在自由射流与真实大气中进气道前和进气道入口处的马赫数分布,确定了3种马赫数下进气道在自由射流中的最佳安装位置。比较发现,亚声速自由射流对真实高空大气飞行进行模拟,可以得到马赫数相似的流场。To predict the characteristics of subsonic flow field in front of aircraft inlet-engine combination in the free jet test of engine altitude simulation and to optimize the aerodynimic configuration of the test ceil, the CFD method has been used to simulate the external flow of a fighter inlet in subsonic free-jet and in the real flight environment in the atmosphere. The relation of compression effect of the inlet to the inflow air and flight Mach number is analyzed. Optimized installation location of inlet has been found in three Mach number of subsonic free-jet. And we compared the Mach number distribution of the forward and entrance of inlet between the condition that in free-jet and in real atmospheric environment. As a result,it can obtain the flow field of similar Mach number that the simulating of real atmospheric flight environment with subsonic free-jet.

关 键 词：自由射流 发动机高空模拟 进气道 马赫数 数值计算 

分 类 号：V216.8[航空宇航科学与技术—航空宇航推进理论与工程]