Abstract
Experiments were carried out to study the effect of plasma flow control on airfoil in an open-circuit low-speed wind tunnel. Lift and drag were measured by a five-component strain gauge balance. Particle image velocimetry (PIV) technology was applied to visualize the flow field over the airfoil. Influence of plasma actuator voltage, electrode position, and control evolution on NACA0015 airfoil was investigated, and the control mechanism was preliminarily analyzed. Lift enhancement validation experiment on NACA23018 two-element airfoil was carried out. The results show that the plasma actuators can efficiently increase the maximum lift and stall angle on a symmetric airfoil and a high-lift airfoil.
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References
He C, Corke TC, Patel MP (2009) Plasma flaps and slats: an application of weakly ionized plasma actuators. J Aircr 46:864–873
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© 2014 Springer-Verlag Berlin Heidelberg
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Wang, X.N., Wang, W.B., Huang, Y., Huang, Z.B., Sheng, Z.H. (2014). Airfoil Flow Control Using DBD Plasma Actuators. In: Zhou, Y., Liu, Y., Huang, L., Hodges, D. (eds) Fluid-Structure-Sound Interactions and Control. Lecture Notes in Mechanical Engineering. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-40371-2_20
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DOI: https://doi.org/10.1007/978-3-642-40371-2_20
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Online ISBN: 978-3-642-40371-2
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