Investigation Of Aerodynamic Forces On NACA Airfoils

Emannuel, Chai (2019) Investigation Of Aerodynamic Forces On NACA Airfoils. Project Report. Universiti Teknikal Malaysia Melaka, Melaka, Malaysia. (Submitted)

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Abstract

The aim of this project is to investigate the aerodynamic force on NACA airfoils by using Computational Fluid Dynamic simulation. ANSYS FLUENT 16 was used as the software for the CFD simulation of NACA 4412 and NACA 4418 in two different turbulence models which are Spalart-Allmaras (S-A) and Transition Shear Stress Transport (SST). The CFD simulation were done in three different air velocities of 10 m/s, 20 m/s and 30 m/s. The angle of attack of the airfoil also varied from 0° to 50° with increment of 5°. These two airfoils were chosen because both different maximum thickness but have the same mean camber line and maximum camber. The airfoil was designed in Solidworks with chord length of 100 mm. A rectangular domain of 300 mm x 300 mm x 450 mm was chosen as the fluid domain to mimic the experiment in wind tunnel with the same dimension of test section. The results for simulated aerodynamic forces between the two airfoils with two different turbulence models were analysed and discussed. Besides, results for the three different air velocity also analysed and the best angle of attack for the airfoils were determine. From the results, the stall angle for both NACA 4412 and NACA 4418 is at 45° for air velocity of 20 m/s and 30 m/s while the stall angle for both airfoils is 40° at 10 m/s. The effect of thickness of the airfoil on aerodynamic forces was also studied where NACA 4418 generate more lift force at its best angle of attack compare to NACA 4412. The performance for NACA 4418 is better than NACA 4412.

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