- #1
physicsCU
- 202
- 1
OK, so the coefficient of lift for a wing is CL.
For an airfoil, it is cl.
How do I go from Lift for an airfoil to Lift for the whole wing? Is it just multiplying by the wingspan?
Thanks!
For an airfoil, it is cl.
How do I go from Lift for an airfoil to Lift for the whole wing? Is it just multiplying by the wingspan?
Thanks!