基于准定常假设的飞行器滚转动导数数值模拟

A Calculation Method of Aircraft's Rolling Dynamic Derivatives Based on Quasi-steady Assumption

文中通过发展的基于求解N-S方程的准定常方法对飞行器动态气动特性中的滚转动导数进行数值模拟研究。对国际标模Finner导弹滚转动导数进行计算验证,并分析了滚转角速度、马赫数以及应用于该方法中的对接面的网格差异对滚转动导数的影响。研究结论表明:数值计算结果与风洞试验值吻合得比较好,规律一致,且该方法耗时少,计算量小,能比较准确快速的得到滚转动导数结果,具有一定的工程实用价值。

A quasi-steady method based on solving N-S equation was developed to calculate roll-damping moment coefficient derivative of aircraft.Finner missile was taken as a typical example,and the roll-damping moment coefficient derivative was calculated,also the effects of mach number,rolling speed and the difference of grids between the interfaces on the derivative were analyzed.The research shows that the numerical result is consistent with experiment data,and the roll-damping moment coefficient derivative obtained by both methods have the same trend;This method costs less time and obtains result quickly,which is propitious to engineering design.