Aerodynamic Performance of NACA 0012 Airfoil with Plain Flap Under Various Conditions

Despite significant advancements in aerodynamic research, recent studies on streamline behavior of airfoils at low-speed conditions remain limited. Understanding streamline characteristics is crucial for optimizing airfoil performance, especially during critical phases such as baseline, lift, stall angle, and stall phase. This study aims to close the gap by examining how NACA0012 airfoil with plain flap and evaluated its corresponding Streamline in critical condition such as its baseline phase, lift phase, stall angle and stall phase. Through a wind tunnel experiment with angles of attack ranging from −20° to 20° and frequencies of 5 Hz, 10 Hz, and 15 Hz, the research seeks to ascertain the stall angle of the NACA 0012. The results revealed critical insights, including the highest lift-to-drag ratio (Cl/Cd) of 3.335 achieved at a wind speed of 15 Hz, an angle of attack (AOA) of 15°, and a flap deflection angle of 15°.