尾缘定常吹气对倾转旋翼机翼型气动性能影响

Effect of Trailing-Edge Steady Blowing on Aerodynamic Performance of Tiltrotor Airfoil

为改善倾转旋翼机气动性能,基于雷诺平均Navier-Stokes方程,采用数值仿真技术研究了尾缘定常吹气控制对倾转旋翼机翼型气动性能的影响。以A821201翼型为基础,系统地讨论了吹气角度、吹气速度和吹气孔宽度等参数对气动力的影响规律。计算结果表明:正角度吹气时,翼型的升力系数和升阻比要小于基础翼型;负角度吹气时,翼型的升力系数和升阻比要大于基础翼型。当吹气角为-45°时,相对于基础翼型,施加尾缘吹气控制后翼型的最大升力系数增加了6.48%,升阻比峰值增加了9.57%。在此基础上,随着吹气速度和吹气孔宽度的增大,翼型的升力系数和升阻比会进一步提升。当吹气速度为60m/s,吹气口宽度0.003C时,8°迎角状态下原来存在于A821201翼型上表面的分离涡完全消失。

In order to improve the aerodynamic characteristics of tiltrotor aircraft,based on the Reynolds-averaged Navier-Stokes equations,the aerodynamic performance of A821201 airfoil with trailing-edge steady blowing control has been computationally investigated.The effects of different factors,including blowing angle,velocity and slot width,are discussed systematically.The results show that the positive blowing angle decreases the airfoil lift and lift-to-drag ratio,whereas the negative blowing angle increases the airfoil lift and lift-to-drag ratio.When the blowing angle is-45°,the maximum lift coefficient is improved by 6.48%and the value of the maximum lift-to-drag ratio is increased by 9.57%compared with the basic airfoil.Additionally,the larger the blowing velocity and slot width,the more obvious its lift-enhancing effect is.With the blowing velocity of 60m/s and the slot width of 0.003C,the flow separation of the A821201 airfoil is completely suppressed at an angle of 8°.