CAJ | 학술논문

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。
위료예측항공발동궤고공모의자유사류시험중비궤진기도-발동궤조합체전방적아성속류장특성，우화시험창적기동설계，채용 CFD 방법재아성속자유사류화진실대기비행조건하대모전두궤진기도적외류장진행수치모의。분석료진기도대전방기류압축작용여비행마혁수관계，대비화분석료분별재자유사류여진실대기중진기도전화진기도입구처적마혁수분포，학정료3충마혁수하진기도재자유사류중적최가안장위치。비교발현，아성속자유사류대진실고공대기비행진행모의，가이득도마혁수상사적류장。
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 cell, 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 num-ber 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.