Is lift/drag the same as coefficient of lift/coefficient of drag? I see it being used interchangeably (for example by Airfoil Tools Fusion360 AddIn), so can I just pick an airfoil from the airfoiltools database with a certain CL/CD for my aircraft and assume L/D is the same?
An example airfoil from the database: clarky-il
(I know there is induced drag as well, which is not calculated in the databse)
I know the formulas, so it makes sense to me. Just want to verify there is not something I am not aware of, in case I want to calculate the lift depending on the angle of attack.
Yes. Lift and Drag are both obtained by multiplying the CL &amp; CD by the same factors (1/2 rho V^2 S); the ratio L/D cancels out those factors, leaving CL/CD.