Experimental and Numerical Investigation of the Control of the Flow Structure on Surface Modified Airfoils

Öztürk, A.; Coban, M.; Koca, F.

doi:10.47176/jafm.16.12.1996

Experimental and Numerical Investigation of the Control of the Flow Structure on Surface Modified Airfoils

Document Type : Regular Article

Authors

Sivas Cumhuriyet University, Sivas, 58100, Turkey

10.47176/jafm.16.12.1996

Abstract

In this study, experimental and numerical flow analysis was performed on three different blade profiles with a chord length of 165 mm using passive flow control method. The first of the airfoil is the standard NACA 0018 profile. The second airfoil type has a NACA 0018 profile with a gap in the suction surface. The last airfoil is the NACA 0018 profile which is 66% of the trailing edge cut from the chord length. All airfoil profiles were analyzed at the Reynolds number, Re=2x10⁴, and angles of attack α=0^o, 5^o, 10^o, 12^o and 14^o in both experiment and numerical studies. The experiments were carried out using the Particle Image Velocimetry (PIV) method in a closed-loop open water channel, and the time-averaged velocity vectors, streamlines, and vorticity contours of the flow field were obtained. Subsequently, numerical analyses were performed using the ANSYS Fluent package program, one of the Computational Fluid Dynamics (CFD) programs used frequently in the literature. The streamlines and pressure contours of the airfoil profiles have been compared visually at the same Re and different angles of attack. In addition, according to the angle of attack of the airfoil profiles, lift coefficient C_L, drag coefficient C_D, and the ratio of lift coefficient to drag coefficient C_L/C_D graphs were presented. It has been shown that the gap on the airfoil at high attack angles caused changes in lift (up to 0.7) and drag (up to 0.15). These features can allow these models to be used for different purposes in the aerodynamics field.

Keywords

Main Subjects

Flow Control

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