摘要
将牛顿碰撞类方法推广应用于超、高超声速细长体导弹的气动特性预测．根据飞行器的外形特征，将外形分成几个部分，根据各自几何特点和流场特性，对不同部分及其迎风面和背风面选用不同的方法，计算方法适用于Ma=3—25、攻角0—30°范围内大长细比导弹类飞行器的气动力特性快速计算．经过与风洞试验数据的对比，证明此方法具有计算速度快、精度高的特点．
Some kinds of Newton＇ s theory of couision methods is extended to calculate the supersonic and hypersonic missiles with large slenderness ratio. These configurations are studied carefully and divided into several parts. Some different methods are applied to calculate the flow field in the windward side and leeward side according to the geometric of missile. The results are got about the aerodynamie characteristics of vehicles with large ratio slenderness under Ma = 3 - 25 and in flow attack angle between 0°- 30°. The comparison of the results are obtained by this method with those from wind tunnel experiments, and it show that this method is fast and aeeurate.
出处
《战术导弹技术》
北大核心
2008年第6期31-35,共5页
Tactical Missile Technology
关键词
超
高超声速
大长细比巡航导弹
气动特性预测
supersonic and hypersonic
missile with large slenderness ratio
aerodynamic prediction
