Please use this identifier to cite or link to this item: http://hdl.handle.net/10397/79049
Title: Enhancement of aerodynamic performance of a heaving airfoil using synthetic-jet based active flow control
Authors: Wang, CL 
Tang, H 
Keywords: Heaving airfoil
Synthetic jet
Vortex manipulation
Issue Date: 2018
Publisher: Institute of Physics Publishing
Source: Bioinspiration and biomimetics, July 2018, v. 13, no. 4, 46005 How to cite?
Journal: Bioinspiration and biomimetics 
Abstract: In this study, we explore the use of synthetic jet (SJ) in manipulating the vortices around a rigid heaving airfoil, so as to enhance its aerodynamic performance. The airfoil heaves at two fixed pitching angles, with the Strouhal number, reduced frequency and Reynolds number chosen as St = 0.3, k = 0.25 and Re = 100, respectively, all falling in the ranges for natural flyers. As such, the vortex force plays a dominant role in determining the airfoil's aerodynamic performance. A pair of in-phase SJs is implemented on the airfoil's upper and lower surfaces, operating with the same strength but in opposite directions. Such a fluid-structure interaction problem is numerically solved using a lattice Boltzmann method based numerical framework. It is found that, as the airfoil heaves with zero pitching angle, its lift and drag can be improved concurrently when the SJ phase angle phi(sj) relative to the heave motion varies between pi/4 and 3 pi/4. But this concurrent improvement does not occur as the airfoil heaves with pi/6 pitching angle. Detailed inspection of the vortex evolution and fluid stress over the airfoil surface reveals that, if at good timing, the suction and blowing strokes of the SJ pair can effectively delay or promote the shedding of leading edge vortices, and mitigate or even eliminate the generation of trailing edge vortices, so as to enhance the airfoil's aerodynamic performance. Based on these understandings, an intermittent operation of the SJ pair is then proposed to realize concurrent lift and drag improvement for the heaving airfoil with pi/6 pitching angle.
URI: http://hdl.handle.net/10397/79049
ISSN: 1748-3182
EISSN: 1748-3190
DOI: 10.1088/1748-3190/aabdb9
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