摘要
为研究气动力对操纵面非定常偏转运动的动态响应,采用非定常雷诺平均N-S方程和基于弧长的超限插值网格更新方法,数值模拟了NLR7301二段翼型襟翼和方形截面导弹一对水平舵的振荡偏转运动。结果表明:基于弧长的超限插值算法能够较好的保持原始网格的正交性、光滑性,实现网格的更新。
To study the response of aerodynamic force to the unsteady oscillation of control surface,an unsteady RANS solver and a deforming grid algorithm based on arc-length-based transfinite interpolation were applied to simulate the flap oscillation of NLR7301 two-element airfoil and the horizontal elevator＇s oscillation of a square section missile.The results show that the deforming grid algorithm can maintain grid orthogonality and smoothness of the original grid.The method in this paper could simulate the hysteresis loop of the aerodynamic characteristics caused by the unsteady pitching motion of the control surfaces.
出处
《弹箭与制导学报》
CSCD
北大核心
2011年第4期207-209,共3页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
操纵面
振荡偏转
超限插值
迟滞
control surface
oscillating deflection
trans-finite interpolation（TFI）
hysteresis
