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通过对柔性尾缘襟翼(DTEF)参数化建模,实现对尾缘襟翼柔性变形与控制。数值模拟DTEF对翼型气动特性的静态及动态情况下的影响,并验证非定常来流下尾缘襟翼对翼型载荷的动态控制效果。研究得出以下结论:DTEF位于不同摆角时,翼型升力系数与阻力系数均有不同程度的明显改变,并随翼型所处攻角的不同改变规律略有变化;DTEF的摆动过程中,翼型升力系数滞后于摆角的变化,DTEF改变升力系数的能力降低;翼型阻力系数超前于摆角的变化,DTEF改变阻力系数的能力增加,襟翼摆动的非定常效应随摆动周期减小而增强;采用跟随风速变化的策略控制尾缘襟翼摆动可有效减缓非定常来流下翼型受力波动。
Through the parametric modeling of the flexible tail flap (DTEF), the flexible deformation and control of the tail flap is realized. The effects of DTEF on aerodynamic characteristics of airfoils are simulated numerically and the dynamic control effects of unsteady tail-flow flaps on airfoil loads are verified. The conclusions drawn from the study are as follows: When the DTEF is located at different swing angles, the lift coefficient and drag coefficient of airfoil vary with different degrees and vary slightly with different changing rules of airfoil angle. During the DTEF swinging process, The lift coefficient of airfoil lags behind the change of swing angle, the ability of DTEF to change the lift coefficient decreases; the drag coefficient of airfoil leads ahead of the change of swing angle, the ability of DTEF to change the drag coefficient increases and the unsteady effect of flap swing decreases with the swing period While the control of tail flap flaps by following the change of wind speed can effectively reduce the fluctuating force of unsteady airfoils.