摘要
非定常数值模拟飞行器的强迫振动过程，获得任意时刻的气动参数，可以解决复杂外形以及多种飞行条件的气动导数问题。通过AVICFD-X软件计算0°-80°初始攻角下的BFM带翼导弹的俯仰动导数，验证该方法的可行性。计算结果与实验值具有很好的一致性，反映了大攻角流场非线性特征。计算中充分考虑了工程实际需求，尽可能地减小计算代价，获得了理想结果，表明该方法适用于复杂外形气动导数计算。
The unsteady numerical method of prescribed motion, which can get all the aerodynamic parameters of any time, was proposed to solve the problems for complex shape aircraft on various lfight conditions. The pitch dynamic derivative of BFM winged missile under 0°-80°initial angle of attack using AVICFD-X software, to comifer the feasibility of the method. The simulation results were in good agreement with the experimental data, which illustrate the nonlinear characteristics of lfow ifeld at large attack angle. Unsteady numerical simulation method implemented in our numerical study considered engineering requirements and obtained good results. Thus, this method is applicable for aerodynamic derivatives on complex shapes.
出处
《航空科学技术》
2015年第8期19-22,共4页
Aeronautical Science & Technology
关键词
非定常流动
气动导数
动态网格
强迫振动
unsteady flow
aerodynamic derivative
dynamic mesh
prescribed motion
