The Effect Of Flap To Aerodynamics Performance Of Airfoil

Zulkefli, Muhammad Dzulzhafrain Ilman (2017) The Effect Of Flap To Aerodynamics Performance Of Airfoil. Project Report. UTeM, Melaka, Malaysia. (Submitted)

Text (24 Pages) The Effect Of Flap To Aerodynamics Performance Of Airfoil.pdf - Submitted Version Download (606kB)

Abstract

Airfoil shapes are designed to provide high lift values at low drag for given flight conditions. Lift is the force generated perpendicular to the direction of travel for an object moving through a fluid (gas or liquid) such as an airfoil in a wind tunnel while drag is the force generated parallel and in opposition to the direction of travel for an object moving through a fluid. Conventional aircraft wings often use moving surfaces (flaps and slats) to adapt to different conditions however this study will just focus on the flap of an airfoil. A NACA 0015 symmetrical airfoil was analyzed to determine the lift and drag coefficient. A 3D airfoil was placed in a test section of a low speed wind tunnel to measure the drag force and lift force. The wind tunnel was operated at a nominal 9.5 m/s. The airfoil, with 130 mm chord and 130 mm span, was analyzed at 0, 5, 10 and 15 degree angles of attack. Besides, this experiment was conducted to compare the result between an airfoil with zero angle of flap and airfoil with angle of flap. Angle of flap has been set at two angle which were 30 and 60 degree angle of flap. Two set of airfoils has been printed for this study. The result shows that airfoil have the highest value coefficient of lift at 60 degree of flap which is 0.664. In addition, throughout the previous research and theoretically, an airplane need a higher value of lift coefficient because once the aircraft is on the ground, the flaps may decrease the effectiveness of the brakes, thus increasing stopping distance, particularly in wet or icy conditions.

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