[Varoesp98]

Hello, I would need that someone send or recommend me somewhere to look for information about how the lift coefficient and the drag coefficient affect in the flaps and slats of an airfoil. The idea is to see the difference between the cl and cd for an airfoil without slats and flaps, and the same airfoil but with slats and flaps. I have already gotten both cd and cl for both of the cases but to make it in a proper way I need some theory to explain it, with formulas and as many things as possible. Please if you can help me I would be very glad because I could not find anything through the internet.

[vinerm]

I am sorry, but your description is not clear. Drag and lift coefficients are just non-dimensionalized forces acting on the solid object along and normal to the flow. So, the explanation is rather simple. Reduction implies reduction in force and increase implies increase. However, to compare the cases, you have to maintain same non-dimensionalization parameter, i.e., same dynamic force should be used despite differences in geometry.

[Varoesp98]

Hello vinerm, what I mean is that I need to read and learn, how those forces are acting when I add flaps or slats to an airfoil, there should be some theory about how they act towards an airfoil, that is what I need, to read and learn about it.

[vinerm]

The forces act independently of the geometry. However, their distribution change as the geometric changes are made. But a force is a force. It pushes and rotates about the center of pressure, provided CP is not same as CG.

[Varoesp98]

okey thanks