Abstract

This study aims to investigate experimentally and numerically the characteristics of the NACA 24112 airfoil. This study focuses on investigations of lift coefficient (C_L), drag coefficient (CD), and C_L / C_D ratio and pressure, including flow visualisation around the airfoil. The study was conducted at an angle of attack ranging to -15°-20° and various Mach number at  0.0728 and 0.0809. The experimental test used a test specimen with a span dimension of 20 cm and a chord of 10 cm with an open wind tunnel. A total of 376,500 square elements with values ∆y + to 9.6 were successfully generated to achieve the accuracy of the simulation. The results showed that the C_L and C_D values obtained from the experimental and simulation results showed a similar trend. The C_D value of the experimental results is greater than the simulation results. The C_L and C_D values will increase with increasing flow velocity and increasing the angle of attack. A stall occurs at an attack angle of 20°.

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