This paper presents the effects of airfoil geometry on flow separation behavior and obtains the transition patterns at a specific angle of attack. A strong adverse pressure gradient field is observed at the leading edge of the airfoil. and it results in a flow detachment. Leading edge flow separation is studied along with the variation of skin friction coefficient over the airfoil. https://ashleyshomestores.shop/product-category/2-piece-reclining-sectional/