Flow analysis of airfoil with mechanical slat and flap using CFD

Chan, Chun Hong (2021) Flow analysis of airfoil with mechanical slat and flap using CFD. Project Report. Universiti Teknikal Malaysia Melaka, Melaka, Malaysia. (Submitted)

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Abstract

Aeroplane have increasingly become an indispensable means of transportation in modern civilization. The design of the airfoil such as slat and flap will affect the fuel consumption and the performance of the aeroplane. Therefore, obtaining a good slat and flap angle of airfoil could increase the performance of aeroplane. In the present work, the numerical analysis lift performance of NACA 0015 airfoil in low Reynold numbers from angle of attack, 0° to 20° has been carried out. The present study aims to improve the lift coefficient of NACA 0015 airfoil. The mechanical slat and flap is designed in order to improve the lift coefficient of airfoil when angle of attack, α= 17°. An optimization of the slat and flap angle is required for design the effective mechanical slat and flap. For NACA 0015 base case with the mechanical slat and flap, there were 3 set of setting, (δ = 15°, β = 25°), (δ = 20°, β = 30°) and (δ = 25°, β = 35°) have been conducted in the simulations. The simulation was performed using CFD program in Ansys Fluent software. The numerical results of lift coefficient, contour of velocity and static pressure around the airfoil have been determined and compared with the results obtained from NACA 0015 airfoil. As a result, the stall angle for NACA 0015 base case and airfoil with mechanical slat and flap is at 17° when air velocity at 10 m/s. Next, the NACA 0015 base case applied the mechanical slat and flap will increase the lift coefficient from at least 62% to 110%. In the simulations, the airfoil with mechanical slat at 20° and flap at 30° obtained the maximum lift coefficient which was 0.3107. Indirectly, the application of slat and flap could increase the critical angle of attack of the airfoil and the area contact between the air and the bottom surface of airfoil. In future, it is recommended that the setting of input and boundary conditions should be applied based on the requirement carefully.

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