The effect of slat and flap to the aerodynamics performance of an airfoil

Abd Hamid, Mohd Sofian (2017) The effect of slat and flap to the aerodynamics performance of an airfoil. Project Report. Universiti Teknikal Malaysia Melaka, Melaka, Malaysia. (Submitted)

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Abstract

This study was dealing with the effect of the application of the leading edge slat and trailing edge flap on the NACA 0015 airfoil. The lift and drag coefficient were determined after some experiments and further calculation based on the theoretical formula. Generally it is about to see the difference of the airfoil characteristic when it is not equipped with the slat and flap and when the airfoil is being equipped with the slat and flap. The experiment took place in a subsonic high velocity wind tunnel. The airfoil was set up at the angle of attack from 0 to 20 with the 5 of interval. The wind tunnel was set with a constant air velocity of 9.5m/s. The indicator panel on the wind tunnel will show the value of lift force and drag force. The data was recorded and the n the experiment is proceed with the replacement of the airfoil with the modified airfoil with the slat and flap. Several configuration of the slat and flap with variety combination of angle of attack was set and tested. The data was recorded. From the test it was found the best angle of attack combination of the slat and flap that is the best for the airfoil. Slat with the angle of 30 with the flap with the angle of 0 gives the best lift force on the airfoil with the value of the lift coefficient of 1.006. hence it can be conclude that the leading edge slat and trailing edge flap can affect the aerodynamic performance of an airfoil.

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