飞行器大迎角下俯仰静、动导数的数值计算

Computation of Vehicle Pitching Static and Dynamic Derivatives at High Angles of Attack

采用一种适用于非定常流动计算的逐次超松弛(SOR)时间推进方法耦合求解非定常Navier-Stokes方程和强迫运动方程,数值模拟了NACA0012翼型、弹道外形(HBS)和有翼导弹等飞行器在不同初始迎角下做强迫俯仰振荡的黏性动态流场,给出动态气动力及力矩系数的时间历程;采用积分法获得飞行器的静导数和动导数,将计算结果与实验结果及半经验理论预测方法进行比较并分析飞行器在大迎角下动态特性的非线性特征;计算结果与实验值相吻合,表明本文采用的非定常数值模拟方法在大迎角下能够较准确地模拟飞行器的动态特性,具有工程应用价值。

A new time-accurate marching successive over-relaxation（SOR）scheme with second order in time for unsteady flow is proposed to solve the Navier-Stokes equation and forced pitching equation in the present work.It is applied to numerically simulating the viscous flow over airfoil NACA0012,hyper ballistic shape and basic finner missile in forced pitching movement at different initial angles of attack.Then the time history of dynamic aerodynamic force and moment coefficients is achieved and the static derivatives and dynamic derivatives of pitching are obtained by integral methods. By comparing the present computational results with the experimental data and computational data obtained through the engineering method, the dynamic nonlinear characteristics are analyzed of vehicles at high angles of attack. The present computational results accord with the experimental data,which indicate that the present method is capable of simulating the dynamic characteristics of vehicles at high angles of attack with accuracy; and it may find wide application in engineering.