A proof-of-concept study is presented to understand the effect of continuous forcing by a dielectric-barrier-discharge (DBD) plasma actuator on the strength of the vortices formed in the tip-gap of a single NACA0065 airfoil. The airfoil was mounted with variable tip gaps in the test-section of a suction-type wind tunnel. Continuous forcing was generated by mounting a straight DBD actuator in the tip gap. The flow field was investigated experimentally by dynamic-pressure measurements, and stereoscopic-particle-image-velocimetry (SPIV). In addition, URANS was performed to investigate the flow field in the tip gap region, where SPIV could not be conducted. The results showed that the effectiveness of forcing decreased with increasing tip-gaps and free-stream velocity. The maximum cancellation of the vortex was observed when the blowing ratio was approximately 0.93, with a tip gap of 0.02c ($c=\text{chord}$) and free stream velocity of 2.7 m/s. Both experimental and numerical results showed that in this particular case, the DBD actuator created a strong reverse flow opposing the direction of tip flow. This reverse flow altered the pressure gradient in the tip gap region and canceled the vortex altogether.

进行了概念验证研究，以了解介电势垒放电（DBD）等离子体激励器持续施加的力对单个NACA0065机翼尖端间隙中形成的涡流强度的影响。机翼以可变的尖端间隙安装在吸风式风洞的测试区域中。通过将笔直的DBD执行器安装在尖端间隙中来产生连续的作用力。通过动态压力测量和立体粒子图像测速（SPIV）实验研究了流场。另外，进行了URANS来研究无法进行SPIV的尖端间隙区域的流场。结果表明，随着叶尖间隙和自由流速度的增加，强迫作用的有效性降低。c（$C=\text{弦}$）和2.7 m / s的自由流速度。实验和数值结果均表明，在这种特殊情况下，DBD执行器产生了与叶尖流动方向相反的强逆流。这种逆流改变了尖端间隙区域中的压力梯度，并完全消除了涡流。