摘要
提出了一种适于在初步设计中使用、具有良好精度的亚、超音速导弹大攻角气动特性的工程计算方法。重点介绍翼-身,尾-身干扰对非线性法向力的贡献,并用抽样作算例,通过翼-身,尾-身干扰因子进行具体计算。结果表明这种方法具有简便,计算快和符合设计精度要求的优点。
An engineering method of aerodynamical computation which apply to preliminary design of sub- sonic and supersonic missiles in large attack angle and have a good precision is presented.the contributions of wing-body and tail-body interference to the nonlinear normal force being stressecl.AS an example,wing-body and tail body interference factor are computed,the result indicate that the method is simple and meets the needs of precision.
出处
《战术导弹技术》
1995年第4期10-17,共8页
Tactical Missile Technology
关键词
导弹
气动性能
大攻角
计算
Missile
Aerodynamic performance
Attack angle
