AERODYNAMIC STUDIES OF FLOW CONTROL METHOD USING UTM AEROLAB NACA-0012 AIRFOIL

Abstract

Many studies have shown that boundary layer tripping is able to delay separation and remove separation bubbles at low Reynolds numbers. However, the effects of boundary layer trip at moderate Reynolds numbers have not yet been well documented. In conjunction to this, the primary objective of this study is to investigate the effect of different transition strip (TS) locations on flow topology on the upper NACA-0012 airfoil and also its corresponding aerodynamic performances at Reynolds number of 1 million. The smooth tape surface is attached at three different locations: 0.0%, 3.8% and 8.8% x/c of the NACA-0012 airfoil. Pressure across the airfoil was measured through electronic pressure scanner. From the results, different strip locations had been shown to affect the flow control above airfoil, which was either to delay or promote separation. Delaying the flow separation can improve lift performance of the wing.