<![CDATA[Symmetric airfoils like NACA 0015 have limitations in generating lift compared to asymmetric airfoils. Therefore, additional devices are needed to overcome this limitation. This research analyzes the use of a lift enhancement device called a plain flap, which is installed on the trailing edge of the NACA 0015 airfoil using the CFD method. Simulations were conducted at a Reynolds number of using the k-epsilon turbulent model. Three variations of geometry models were simulated: the NACA 0015 airfoil without a flap, the NACA 0015 airfoil with a plain flap at a deflection angle of 15°, and the NACA 0015 airfoil with a plain flap at a deflection angle of 30°. The simulation results show that the use of a flap can increase the maximum lift coefficient (Cl) of the airfoil. Initially, the maximum lift coefficient was 1.15 at an angle of attack (AoA) of 15°. With a plain flap deflection angle of 15°, the maximum lift coefficient increased to 1.5 at an AoA of 13°. With a plain flap deflection angle of 30°, the maximum lift coefficient further increased to 1.71 at an AoA of 10°. However, the use of a plain flap also leads to a significant increase in drag. On average, the drag coefficient (Cd) increased by 65% with a plain flap deflection angle of 15° and by 178% with a plain flap deflection angle of 30°.]]>
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