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Experimental and computational study of airfoil load alteration using oscillating fence actuator.

机译：利用摆动栅栏致动器改变翼型载荷的实验和计算研究。

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Experimental and computational studies have been conducted for characterizing the effect of a fence actuator on stationary and oscillating airfoils and assessing the authority of the fence actuator for altering the aerodynamic loading of an airfoil to suppress flutter. In particular, an oscillating fence on a NACA-23012 airfoil has been examined using Particle Image Velocimetry (PIV), time-resolved pressure measurements, and numerical simulations of a pitching airfoil. Experiments over stationary and oscillating airfoils show that the fence frequency strongly affects the evolution of the vortical structures generated by the fence and that higher actuation frequencies are more effective in producing higher suction peaks. For an oscillating airfoil, variation of the mean angle of attack strongly affects the baseline pressure distribution as expected. The disturbances, however, remain largely unaffected by the variations in mean angle of attack. It was also observed that the adverse pressure gradient at higher angles of attack caused a reduction in dissipation of the disturbances. Integrated lift and moment are used to quantify the effectiveness of the fence actuator, and the sufficiently large changes produced in these quantities show the potential of this device for altering the aerodynamic loading of a wing and suppressing flutter. Results from the computational study indicate that the fence is capable of producing significant disturbances that diminish airfoil oscillations, more so when the actuator is located close to the trailing edge. Implementation of an appropriate control scheme can be used to enhance the effects of these actuators.;Pressure Sensitive Paint experiments conducted for better understanding the production and evolution of the disturbances revealed complex surface pressure behavior. The results indicate that the actuator disturbances develop three-dimensionality soon after the fence penetrates the flow because of the finite fence length effects. Furthermore, the structure was found to evolve faster for slower fence frequencies due to reduction in time scale imposed by the oscillating fence. These results also suggest that the use of a two-dimensional disturbance in the numerical model may have caused over-estimation of the effect of the actuator.
机译：已经进行了实验和计算研究，以表征栅栏致动器对固定翼片和振荡翼型的影响，并评估栅栏致动器改变翼型的气动载荷以抑制颤动的权威。特别是，已经使用粒子图像测速（PIV），时间分辨压力测量和俯仰翼型的数值模拟检查了NACA-23012翼型上的摆动栅栏。在固定翼片和振荡翼片上进行的实验表明，围栏频率强烈影响围栏产生的旋涡结构的演变，较高的驱动频率在产生较高的吸力峰方面更有效。对于振荡的机翼，平均攻角的变化会严重影响基线压力分布。但是，这些干扰基本上不受平均攻角变化的影响。还观察到，较高攻角处的不利压力梯度导致干扰消散的减少。集成的升力和力矩用于量化围栏致动器的有效性，并且在这些量中产生的足够大的变化表明该设备具有改变机翼的空气动力学载荷并抑制颤振的潜力。计算研究的结果表明，围栏能够产生显着的扰动，从而减小翼型的振动，当执行器位于后缘附近时，这种情况更为明显。可以使用适当的控制方案来增强这些执行器的效果。为了更好地理解扰动的产生和发展而进行的压敏涂料实验揭示了复杂的表面压力行为。结果表明，由于围栏长度有限的影响，致动器扰动在围栏穿透水流后很快就产生了三维。此外，由于振动围栏所施加的时间尺度的减少，发现该结构在较低的围栏频率下发展更快。这些结果还表明，在数值模型中使用二维干扰可能会导致对执行器作用的估计过高。

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