FSAE尾翼翼型的空气动力学研究

Study on Aerodynamic Effects of FSAE Rear Airfoil

针对尾翼的翼型参数和翼布置进行二维翼型的仿真,根据设计目标在Profili翼型库中筛选获取所涉及的翼型。通过CATIA建立流体域模型,采用空间布点的方式设定网格的增长方式。导入Fluent中进行仿真,对翼型在不同情况下的气流流线、所受静压、流速等进行研究,得出如下结论:GOE482翼型作为主翼时的弯度可以取8%以上,襟翼的弯度不宜太大,可以取弯度为4%左右的翼型,翼型最大弯度和最大厚度所在位置后移可以提高气流附着能力。

This paper carries out the two-dimensional airfoil simulation for the airfoil parameters and airfoil layout of the rear wing.The involved airfoil is selected from the Profili airfoil library according to the design objectives.The fluid domain model is established by CATIA,and the mesh growth mode is set by means of inserting points in fluid domain.The model is introduced into Fluent for simulation to study the flow line,static pressure and velocity of the airfoil under different conditions.The following conclusion can be drawn:when the GOE482 airfoil is used as the main wing,the camber can be taken as more than 8%,and the camber of the flaps should not be too high.An airfoil with a camber of about 4%can be taken.The maximum camber and maximum thickness of the airfoil can be moved back to improve the airflow adhesion ability.