摘要
本文介绍一种计算中等攻角、中等侧滑角情况下正常式或鸭式布局的战术弹纵、横向气动力特性的方法。它是一种数值计算与工程计算相结合的方法。位流气动力通过求解线性偏微分方程获得,粘性分离产生的非线性气动力通过对一系列脱体涡的计算获得。方法中考虑了翼面与尾面间近距干扰和远距干扰的影响。本方法可用于计算来流马赫数为0到3.5左右、攻角和侧滑角为0°到20°左右、正常式或鸭式布局的战术弹纵、横向气动力系数。计算结果与实验数据比较,有良好的一致性。
A method for calculating longitudinal and lateral aerodynamic characteristics is presented for conventional and canard configurations of tactical missils at high angle of attack and high yawing angle. This is the method of combining the numerical computation with engineering calculation. The aerodynamic characteristics of the potential flow are obtained with solving linear partial differintial equation, while nonlinear aerodynamic characteristics due to viscousity are obtained using the calculation of the shed-body vortex system. The effects of neardistance and far-distance interference between wings and tails are considered in this method. The longitudinal and lateral aerodynamic characteristics of tactical missiles for the conventional and canard configuration can be calculated using this method at Mach number range from 0 to 3.5, angle of attack and yawing angle from 0 to 20 degrees. The computational results and experiment data have reasonable agreement.
出处
《空气动力学学报》
CSCD
北大核心
1991年第4期394-401,共8页
Acta Aerodynamica Sinica
关键词
战术导弹
纵横向气动力
计算
导弹
tactical missile, longitudinal and lateral aerodynamic characteristics, computation.
