This study numerically evaluates the performance of flow control using fluidic oscillators on the NACA 0015 airfoil with a flap at different flap angles and different pitch angles of the oscillators. An inline array of fluidic oscillators is located just in front of the flap. Aerodynamic analysis was carried out using three-dimensional unsteady Reynolds-averaged Navier-Stokes equations in a computational domain that consists of the external domain around the airfoil and the internal domains in three fluidic oscillators. Flap angles of 20°, 40°, and 60° were tested with a fixed angle of attack of 8°. For each flap angle, the effects of the pitch angle of the oscillators on the aerodynamic performance were evaluated in a range of 60° to the negative value of the corresponding flap angle. It was found in this work that the oscillator jets parallel to the flap showed the best performance, which was achieved by using negative pitch angles and also bending the outlets of the oscillators. The results indicate that the aerodynamic performance varies significantly with the flap and pitch angles.

这项研究在数值上评估了使用流体振荡器在具有不同襟翼角和不同俯仰角的襟翼的NACA 0015机翼上的流动控制性能。串联的流体振荡器位于襟翼的正前方。空气动力学分析是在计算域中使用三维非稳态雷诺平均Navier-Stokes方程进行的，该计算域由翼型周围的外部区域和三个流体振荡器的内部区域组成。测试了20°，40°和60°的襟翼角，固定攻角为8°。对于每个襟翼角，在60°到相应襟翼角的负值范围内评估了振荡器的俯仰角对空气动力性能的影响。在这项工作中发现，平行于襟翼的振荡器射流表现出最佳性能，这是通过使用负俯仰角并弯曲振荡器的出口来实现的。结果表明，空气动力性能随襟翼和俯仰角的变化而显着变化。