- #1
heinekenisnic
- 3
- 0
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.
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.