Experimental Control of Vortex Breakdown by Pulsed Blowing Over a Delta Wing With Rounded Leading-Edge

Abstract

The purpose of this study is to construct and test an experimental device to control vortex on a delta wing. The model has a root chord of c = 690mm and a sweep angle of Λ = 60°. The control system is based on four rectangular slits 50 mm long and 0.2 mm wide running along the leading edge. This configuration produces jets normal to the leading edge. The mass flow rates and frequencies of injection can be varied independently. The results are shown in the form of surface flow visualizations, with the skin friction pattern exhibited by oil flow visualization, and the laminar-to-turbulent transition by acenaphthene. Mean and instantaneous surface pressure distributions were determined with Kulite™ sensors and the velocity field was determined by 3D laser Doppler velocimetry (LDV) measurements. Control device efficiencies were evaluated by laser sheet visualization.

Low Reynolds Number Flow Dynamics of a Thin Airfoil with an Actuated Leading Edge

“…10 Direct numerical studies 14,15 on flow over cylinders have shown considerable reduction in lift variation by using suction to control the vortex shedding. There is a large literature dealing with pulsed and synthetic jets, [16][17][18][19][20] plasma discharge based actuation [21][22][23][24][25][26] for flow control applications resulting in increased lift-to-drag ratio.…”