Experimental Investigation of the Flow Field around NACA0012 Airfoil

Abstract

In this study, an experimental investigation of the flow field around NACA0012 airfoil was carried out in a wind tunnel under the effects of the Reynolds number and angle of attack. The Reynolds number based on the chord length of airfoil and the attack angle was varied from 9.7x10 to 1.9x10 and 0 to 14 respectively. Mean velocities were measured by a… (More)

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