Hi,

Solidworks is quite new to me and I need some help to calculate the drag and lift coefficients of my modified naca airfoil. I worked at school with flow simulation and obtained data about X (Drag) and Y (Lift) forces. I know there are physical formula to calculate Drag and Lift coefficient. However, my X and Y forces vary a lot and I'm really upset by this. How can I find the drag and lift coefficient with this ?