摘要
通过数值模拟方法研究了吸气式导弹尾部喷流对底部阻力的影响。采用内通道截断方法进行热喷状态下流场数值计算,获得了热喷状态下底部干扰流场结构和底部阻力系数,同时研究了燃气属性对热喷效应的影响。最后与冷通气状态流场计算结果进行比较,进一步分析了热喷效应的影响机理。计算结果表明,热喷效应和燃气属性都会对导弹底部阻力产生极大影响。
The influence of afterbody jet on the base drag of an air breathing missile is investigated by numerical simulation. An inner disjointed method is adopted to calculate hot jet flow fields, and the base interaction flow structure and base drag coefficients under hot jet condition are obtained. The influence of motor fluid properties on the base drag is also studied. At last, compared with cold flow through fields, the influence mechanism of hot jet effect is analyzed. Numerical results indicate that the hot jet effect and the motor fluid properties both affect the base drag greatly.
出处
《现代防御技术》
北大核心
2009年第5期25-29,共5页
Modern Defence Technology
关键词
吸气式导弹
尾部喷流
底部阻力
数值模拟
suck-down（air breathing） missile
tail（afterbody） jet
base drag
numerical simulation
