摘要
提出某型号飞机的简化机身研究思路,对研究区域分区划分网格,采用相对坐标方式数值模拟了两种大气湍流尺度下,飞机在8km高度下以0.8Ma飞行时的尾喷流速度场和CO2浓度场特性。计算结果表明速度场在尾喷口衰减很快,而浓度场衰减相对较慢。远离喷口的尾喷流分布主要受大气条件如湍流、分子扩散的影响。
The research measure of simplify fighter plane body is proposed in this paper.The whole research area grid is divided into different part areas.Given the settings of the fighter plane is flying in the 8 km altitude and the velocity is 0.8Ma,with the relative coordinate and two scales of atmosphere turbulence,the fighter plane plume features of velocity field and CO2 concentration field are numerical simulated.The results show that the velocity attenuation is very fast in jet spout,whereas the concentration ...
出处
《微计算机信息》
北大核心
2008年第7期257-258,共2页
Control & Automation
基金
武器装备探索研究项目(项目编号不公开)
关键词
飞机
尾喷流
速度场
浓度场
数值模拟
fighter plane
plume
velocity field
concentration field
numerical simulation
