The Effects of Reynolds Number on Flow Separation of Naca Aerofoil

Abstract

The purpose of this study is to investigate the flow separation above UTM 2D Airfoil at three different Reynolds numbers which are 1 × 10  , 1.5 × 10  and 2 × 10  using pressure distribution method and flow visualization. The experiment was conducted in UTM-LST (Low Speed Tunnel). The pressure distribution is done on three different wing span, which are 40%, 50% and 70%m of span and was measured and plotted to observe the flow characteristic at angle of attack from 0° to 35° for all three different Reynolds numbers. The flow visualization method was done at 10m/s, 20m/s and 30m/s airspeed from 0° to 18°. It is concluded that the Reynolds number of 1 × 10  separates at 16°; Reynolds number of 1.5 × 10  separates at 18° and Reynolds number of 2 × 10  separates at 20°.