摘要
基于"第一届CHN-T1标模CFD可信度研讨会"的相关计算安排,采用CFL3D求解器结合组委会提供的结构网格进行CHN-T1标模的气动特性计算。对比发现CFL3D求解器的SST湍流模式相对SA模式具有更好的网格收敛性。对标模的抖振特性进行了分析,发现抖振起源于机翼中段的激波/边界层干扰,进入抖振状态后当迎角继续增大,激波将持续增强,同时外翼段的后加载减小,使得低头力矩下降,操纵特性变差。对静气弹效应进行了分析,发现该效应主要影响了变形较大位置的升力系数以及激波强度。大雷诺数下机翼截面压力分布后加载包围的面积增大,机翼上表面超声速区的吸力平台有所下降。
Based on the computational tasks of the“1 st Aeronautics CFD Credibility Workshop(AeCW-1)”,the aerodynamic performance analysis of the standard model CHN-T1 is evaluated using the provided structured grid and CFL3D flow solver.The grid convergence results show that the SST turbulence model has better performance than the SA model.The buffet study shows that the interference of shock wave/boundary layer appears from the middle of the wing span,and the shock wave continues to increase its strength with increasing angle of attack.The aft loading decreases rapidly in buffet state,which causes the deterioration of control performance.The elastic deformation mainly effects the strength of shock wave and lift distribution in span direction.Under the condition of large Reynolds number,the aft loading area of the pressure coefficient increases,and the suction platform of pressure coefficient decreases,leading to a low drag coefficient.
作者
李浩然
李亚坤
张宇飞
陈海昕
LI Haoran;LI Yakun;ZHANG Yufei;CHEN Haixin(School of Aerospace Engineering,Tsinghua University,Beijing 100084,China)
出处
《空气动力学学报》
CSCD
北大核心
2019年第2期329-336,共8页
Acta Aerodynamica Sinica
基金
国家自然科学基金项目(11872230
91852108)
清华大学自主科研项目(2015Z22003)
