战术弹亚声速纵横向非线性气动力计算研究

A Numerical Method Study of Longitudinal and Lateral Aerodynamics at Subsonic Speed for Tactical Missiles

基于势流方程，进一步发展了非线性涡格法，计算研究了“ＸＸ”布局战术弹的纵横向非线性气动性能；与实验数据比较表明，本法适用于Ｍ∞≤０．８，α∞≤１５°。由于该法只需要在物面上划分网格，涡迹的松弛迭代都不超过３０次，使得该法具有适应性广、省机时、使用方便、计算准确的特点。每次计算能详细提供各部件的气动干扰性能以及分离涡的强度和位置，成为气动外形设计、研究的有力手段。

Based on the potential flow equation,the nonlinear vortex lattice method is developed,and used to compute longitudinal and lateral nonlinear aerodynamics of a tactical missile in “XX” arrangement.The comparison with exparimental data shows that this method is suitable to range of M ∞≤0.8 and α ∞≤15°.It is characterised by the benefits of calculating accuracy,calculating efficiency,low cost and convenience for application,due to dividing the computing grid just on the surface,to reaching the solution convergence for relaxed itreation is not more than thirty times,and it will be a powerful tool for designing the aerodynamic configurations because it is easy to obtain aerodynamic interference for components in combination and positions of vortical wake.