Analysis of Airfoil NACA: A Computational Fluid Dynamics Approach

An airfoil is a cross-section of an aeroplane wing which is having a curved surface so that it will provide coefficient of lift (Cl) and coefficient of drag (Cd) which is most important factors required for aeroplane flight by the aeroplane wings or the generated forces may also be used by propeller blades etc. when the shape of the airfoil changes their aerodynamic characteristics also change. The airfoil is also very useful because it suspends completely bulky weight of airplane in air. Therefore the design of airfoil is when moved with certain required speed it produced some useful aerodynamics characteristics due to the relative motion between the airfoil and the air as a medium. The force generated by the help of pressure difference (perpendicular) is the lift force acting on the airfoil and the force generated due to the shear force (parallel) is known as drag force which is in opposite direction of motion of aeroplane resulting more consumption of energy to overcome this force. The CFD analysis of airfoil has been conducted to optimize the angle of attack to get maximum Coefficient of lift (Cl) and at that corresponding angle effect of Coefficient of drag (Cd).