S801翼型在不同腐蚀深度下的气动性能

本文通过数值模拟的方法,在前缘不同腐蚀深度的情况下,研究S801翼型的气动性能。结果表明:在低攻角下,随着翼型前缘腐蚀深度的增加,翼型的升力系数计算值与实验值比较吻合。在高攻角时,由于失速现象的产生,随着腐蚀深度的加深,计算结果明显小于实验结果。

In this paper,the aerodynamic performance of the S801 airfoil is studied by numerical simulations under different corrosion depths of the leading edge.The results show that at low attack angles,as the leading edge corrosion depth of the airfoil increases,the calculated lift coefficient of the airfoil is in good agreement with the experimental value.At high angles of attack,due to the stall phenomenon,the calculation results are significantly smaller than the experimental results as the corrosion depth deepens.