飞机发动机尾流流场数值模拟与红外特性计算  

Numeric simulation of flow field and calculation of IR characteristics for aircraft engine

作　　者：吴沿庆 廖守亿 张作宇 花超 

机构地区：[1]火箭军工程大学测控工程系,陕西西安710025

出　　处：《激光与红外》2017年第11期1380-1385,共6页Laser & Infrared

摘　　要：建立飞机尾喷管的三维几何模型,利用Fluent 6.3.26软件对喷管外的流场区域进行数值模拟,基于发动机完全燃烧假设得到尾焰流场温度、压强等流场数据。利用K-分布法计算尾焰气体辐射参数,采用反向蒙特卡洛法(RMC)对气体红外辐射特性进行了计算,最终获得尾焰的红外辐射图像。The 3 D geometric model of airplane tail nozzle is established, and the numerical simulation of the flow fieldoutside the nozzle is carried out by Fluent 6. 3.26 software. The flow field data of tail flame such as temperature andpressure are obtained based on the assumption of engine complete combustion. The K - distribution method was usedto calculate the radiation parameters of the tail flame. The infrared radiation characteristics of the gas were calculatedby Reverse Monte Carlo method （ RMC）, and the infrared radiation image of the tail flame was obtained.

关 键 词：尾流 FLUENT K-分布法 反向蒙特卡洛法 红外辐射特性 

分 类 号：TN219[电子电信—物理电子学]