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为得到适用于平流层螺旋桨桨叶叶素的翼型,采用数值方法,通过改变气流速度和攻角,比较研究了低雷诺数下8种典型翼型的非定常气动性能。结果显示,大攻角工况下翼型容易发生流动分离现象,翼型吸力面的分离越严重,气动力的振荡幅度越大。通过比较不同攻角和不同速度下翼型的升阻比大小和气动稳定性得出,SD8000-PT翼型具有较高的升阻比和较稳定的气动力,适合作为螺旋桨的翼型。
In order to obtain the airfoils suitable for the stratospheric propeller blade, the unsteady aerodynamic properties of eight typical airfoils at low Reynolds number are studied by numerical methods and by changing the air velocity and angle of attack. The results show that the airfoil is prone to flow separation under the condition of large angle of attack, and the more serious the separation of airfoil suction surface, the larger the amplitude of aerodynamic oscillation. By comparing the lift-drag ratio and the aerodynamic stability of airfoils at different angles of attack and different speeds, the SD8000-PT airfoil has a higher lift-drag ratio and a more stable aerodynamic force, and is suitable as a propeller airfoil.