Recent content by heinekenisnic

Homework Statement Why does the lift curve, Coefficient of lift plotted against angle of attack, go through the origin of the graph for some airfoils but not for other airfoils Homework Equations The Attempt at a Solution

hi, I am required to search the internet to find out what the theoretical value of the lift slope (dcl/dalpha) is for thin airfoils. Cl is the lift coefficient and alpha is the angle of attack of the airfoil. Does anyone have any ideas? Thanks for your time.