The Effects of Reynolds Number on Flow Separation of Naca Aerofoil
Keywords:
UTM 2D Aerofoil, Wind Tunnel Experiments, Flow Visualization , Flow SeparationAbstract
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°.