The effects of reynolds number on flow separation of Naca Aerofoil

• Main Authors: Ab. Wahid, Mastura, Abdul Hakim, Muhammad Syahmi, Dahalan, Md. Nizam, Mansor, Shuhaimi, Wan Ali, Wan Khairuddin, Othman, Norazila, Mat, Shabudin
• Format: Conference or Workshop Item
• Published: 2018
• Subjects: TJ Mechanical engineering and machinery
• Online Access: http://eprints.utm.my/id/eprint/82461/

The purpose of this study is to investigate the flow separation above UTM 2D Airfoil at three different Reynolds numbers which are 1 × 106, 1.5 × 106 and 2 × 106 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 × 106 separates at 16° Reynolds number of 1.5 × 106 separates at 18° and Reynolds number of 2 × 106 separates at 20°.