- #1
PHstud
- 12
- 0
Hello everyone.
I have a question about the fact that there is no drag in the thin airfoil theory. I have read that it comes from inviscid and incompressible flow (potential flow) but what i can not understand is why there would be no drag from pressure differences ?
The skin drag is of course 0 since the flow is inviscid, but if i imagine the flow around a angled thin airfoil, I would think that the projection of the pressure on the flow direction (let's say x) would create a drag force !
Also, I do not understand why adding viscosity/Boundary layer would all of sudden allow the pressure drag to exist ?
Thank you !
I have a question about the fact that there is no drag in the thin airfoil theory. I have read that it comes from inviscid and incompressible flow (potential flow) but what i can not understand is why there would be no drag from pressure differences ?
The skin drag is of course 0 since the flow is inviscid, but if i imagine the flow around a angled thin airfoil, I would think that the projection of the pressure on the flow direction (let's say x) would create a drag force !
Also, I do not understand why adding viscosity/Boundary layer would all of sudden allow the pressure drag to exist ?
Thank you !