摘要
阻尼动导数计算时,常常采用基于旋转参考坐标系的准定常计算方法,传统方法直接计算滚转阻尼动导数时,不能考虑速度相对旋转轴存在垂直分量的影响。本文对传统方法进行改进,通过将飞机的速度矢量分解为垂直于旋转轴和平行于旋转轴两个分量,以垂直于旋转轴的速度分量计算旋转半径并推算参考坐标系的旋转中心点,以平行于旋转轴的速度分量作为来流速度矢量计算气动力系数,通过计算不同角速度的气动力系数之差求得动导数。考虑DLR-F12和TCR两个标准模型的阻尼动导数,并与传统方法以及风洞试验数据进行对比,结果表明改进方法考虑了速度垂直分量对滚转阻尼动导数的影响,可推广至任意来流方向和旋转方向的阻尼动导数计算,相对于传统方法计算量减半,改进方法是有效的、准确的。
The quasi-steady damping derivatives computation method based on rotation reference frame is improved aimed at the limitation of damping dynamic derivatives computation when computing roll damping derivatives with a non-zero angle of attack.In this method,the velocity vector is divided into two parts,one perpendicular with X-axis and the other parallels with X-axis.The rotation radius and rotation center are computed using the perpendicular part of velocity vector with X-axis,and set the parallel part as the freestream velocity to compute aerodynamic coefficients.The dynamic derivatives are computed by computing the difference of aerodynamic coefficients with two different angular velocity.This method can reduce the computation time of roll damping derivatives with a non-zero angle of attack and can extend to the damping derivatives computation with arbitrary velocity and rotation direction.The DLR F12 and TCR standard model is used to verify the improved method and the results are compared with wind-tunnel test,former method and other numerical results.Results show that our method is applicable for Euler and RANS computation,and has a high coincidence with former method,which can reduce the computation time for parts of cases.
作者
吴耕宇
鲍君波
宋万强
相倩
Wu Gengyu;Bao Junbo;Song Wanqiang;Xiang Qian(Chinese Aeronautical Establishment,Beijing 100012,China)
出处
《航空科学技术》
2022年第7期95-105,共11页
Aeronautical Science & Technology
关键词
计算流体力学
阻尼动导数
准定常
旋转坐标系
computational fluid dynamics
damping derivatives
quasi-steady
rotation frame
