Abstract
The design structure of an aircraft is highly dependent on load factors. The loads acting on the wing of an airplane include aerodynamic loads, fuel weight and loads due to the weight of the wing structure. But of all the loads that work, aerodynamic loading is the largest load that must be accepted by the wing of the entire aircraft structure which is influenced by the pressure distribution. The purpose of this study is to determine the effect of pressure distribution on the NACA 653-218 airfoil at various variations of angle of attack with a comparison using wind tunnel experimental trials using solidwork software simulations. The largest pressure distribution generated based on wind tunnel experimental trials is at an Angle of Attack of 15 ° of 101326.73pa on the Upper Surface Airfoil, while the largest pressure distribution generated based on solidwork software simulations is at an Angle of Attack of 15 ° of 101690.01pa on the lower Surface Airfoil.
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