CFD Simulation Of 3-D Flow Field Over Clean And Loaded Wing

The phenomenon of flow separation have long been a concern in the aviation field as it could cause many aviation issues such as aircraft stalling during take-off or landing which could lead to airplane crashes and fatality. This problem can become more severe in the high speed fighter jets. So far, very little have been reported on the on the visualization and analysis of the flow fields interaction of wing with load, such as drop tank or missile. This project aims to investigate the effect of airfoil configuration towards the occurrence of flow separation. The effect clean and loaded airplane wings or airfoils at several angle of attacks towards the severity of the flow separation was investigated. Furthermore, the amount of lift and drag force when the clean and loaded wing subjected to air flow at different angle of attack were also predicted. NACA 4412 airfoil was selected for this study via computational fluid dynamics (CFD) simulation in order to study the behavior of flow field over clean and loaded airfoils at angle of attack (AOA) of 0, 15, 17.5 and 20 degrees. Based on the initial simulation conducted upon clean and loaded airfoil at 0 degree angle of attack the pressure on the surface of the airfoil was predicted and presented via pressure contour, velocity magnitude as well as the lift and drag force that acts upon the scaled down computational solid model of the NACA airfoil. Next step is the study regarding this topic with greater detail at the other angle of attack.