基于定常NS方程的飞行器滚转阻尼力矩系数导数计算方法

A Calculation Method of Aircraft Roll-damping Moment Coefficient Derivative Based on Steady NS Equation

文中在物面无滑移边界条件的基础上施加物面绕体轴的切向速度,通过求解定常NS方程对飞行器滚转进行模拟。基于滚转力矩对滚转角速度的展开,发展了一种基于求解定常流场的滚转阻尼力矩系数导数计算方法。该方法物理意义比较明确,由于避免了求解非定常流场,计算量小,速度快。通过对导弹标模的计算值与实验值的对比分析表明,计算结果均在实验值的误差带之内,变化趋势比较一致,因此该方法可以用于工程设计。

In the paper, the steady NS equation was solved to simulate aircraft roll by adding tangent velocity to no slip wall boundary condition. The calculation of aircraft roll-damping moment coefficient derivative was discussed based on steady flow because roll moment is almost linear with roll angular velocity. The method＇s physical meaning is relatively explicit, and time cost was reduced without solving unsteady flow. The computational result of a standard missile model with this method is well agree with the experimental data found in a foreign public lecture and is within experimental error range. So the method can be applied to engineering design.