某战斗机尾喷管外壁面温度场仿真建模研究  

Simulation Modeling Study of the Nozzle Outer Wall Temperature Distribution of Fighter

作　　者：王杏涛[1] 祁鸣[1] 张二磊[1] Wang Xingtao;Qi Ming;Zhang Erlei(China Airborne Missile Academy, Luoyang 471009, China)

机构地区：[1]中国空空导弹研究院,河南洛阳471009

出　　处：《航空兵器》2018年第2期60-64,共5页Aero Weaponry

基　　金：航空科学基金项目(20160112003)

摘　　要：战斗机在飞行过程中,由于高温尾焰热辐射及发动机内部的传热作用,在尾喷管外壁面接近喷管出口位置会形成一个温度较高的区域,进一步增强战斗机的红外辐射信号,进而降低其红外隐身性能。本文在飞行条件下某战斗机机身外流场和喷管流场建模仿真基础上,对战斗机尾喷管外壁面温度场分布进行数值计算,得出了尾喷管外壁面温度场的分布规律及其内部热传导的分布特点,并与试验测试的尾喷管温度分布图像进行对比验证。In the flight of the fighter, a hot area forms near the nozzle exit position because of the thermal radiation of the high temperature tail flame and the engine internal heat transfer. As a result, the fighter＇ s infrared radiation signal will be enhanced and the infrared stealth peffomlance will be reduced. Based on the simulation modeling of fuselage external flow field and nozzle internal flow field in fighter flight condition, the nozzle outer wall temperature distribution rule and the characteristics of internal ther- mal conduction are obtained by numerical calculation. The results are verified by comparing with the ex- perimental results.

关 键 词：尾喷管外壁面 建模仿真 内部导热 温度分布 试验验证 

分 类 号：V271.41[航空宇航科学与技术—飞行器设计] E926.31[军事—军事装备学]