Experimental investigation of plasma vortex generator in flow control
Aircraft Engineering and Aerospace Technology
ISSN: 0002-2667
Article publication date: 3 January 2019
Issue publication date: 19 March 2020
Abstract
Purpose
The purpose of this paper is to compare the effects of two different configurations of plasma streamwise vortex generators (PSVG), including comb-type and mesh-type in controlling flow. This is demonstrated on the NACA 0012 airfoil.
Design/methodology/approach
The investigations have been done experimentally at the various electric and aerodynamic conditions. The surface oil flow visualization method has been used to the better understanding of the flow physics and the interaction of the oncoming flow passing over the airfoil and the vortex generated by comb-type PSVG.
Findings
This paper demonstrates the potential capabilities of the mesh-type and comb-type PSVGs in controlling flow in unsteady operation. It was found that the vortex generated by the mesh-type PSVG in unsteady operation was an order of magnitude stronger than comb-type PSVG. The flow visualisation technic proved that only a part of the plasma actuator is effective in the condition that the actuator is installed only on a portion of the upper surface of the airfoil.
Originality/value
This paper experimentally confirms the capabilities of the mesh-type PSVG unsteady operation in compare with comb-type PSVG in controlling flow, whereby recommends using mesh-type PSVG in the leading edge in front of comb-type PSVG on the entire wingspan to prevent the stall.
Keywords
Citation
Ghayour, A. and Mani, M. (2018), "Experimental investigation of plasma vortex generator in flow control", Aircraft Engineering and Aerospace Technology, Vol. 92 No. 3, pp. 376-385. https://doi.org/10.1108/AEAT-07-2018-0194
Publisher
:Emerald Publishing Limited
Copyright © 2019, Emerald Publishing Limited