A parametric numerical study is conducted to assess the effect of trajectory nature on the propulsive performances of a NACA0014 flapping airfoil. Sinusoidal and non-sinusoidal plunging and pitching trajectories are combined to achieve sought flapping trajectories. To this aim, the effect of kinematic parameters such as oscillation frequency, plunging amplitude, pitching amplitude, and phase angle between pitch and plunge is evaluated on thrust and propulsive efficiency behavior at a low Reynolds number, \(Re=1.1\)x\( 10^4\). It is found that the best propulsive efficiency is obtained for sinusoidal paths, while non-sinusoidal ones are found to slightly improve thrust and lift forces. Furthermore, thrust coefficient maximum values are obtained for non-sinusoidal trajectories when flatness coefficients \(S>1\). The highest lift coefficient values are found however for flapping trajectories when flatness coefficients \(S<1\).

进行了参数数值研究，以评估弹道特性对NACA0014扑翼型机翼推进性能的影响。正弦曲线和非正弦曲线的俯冲和俯仰轨迹相结合，以实现所需的拍打轨迹。为此，在低雷诺数\（Re = 1.1 \） x \下，评估了运动学参数（例如，振荡频率，下降幅度，俯仰幅度以及俯仰和俯冲之间的相位角）对推力和推进效率行为的影响。 （10 ^ 4 \）。发现正弦曲线路径具有最佳的推进效率，而非正弦曲线路径则略微改善了推力和升力。此外，当平坦系数\（S> 1 \）时，获得非正弦轨迹的推力系数最大值。但是，当平坦度系数\（S <1 \）时，对于拍打轨迹找到最高的升力系数值。