Aerowerx
Well-Known Member
I have read here on HBA, and elsewhere, that the coefficient of lift on a swept wing changes with the sweep.
There is an equation given, something like cl1=cl2/cos2(theta), where theta is the sweep angle.
Ok, if you have an airfoil with a certain section lift coefficient, does this mean that you have to use a higher lift coefficient to get the desired lift? Or is it the other way around?
There is an equation given, something like cl1=cl2/cos2(theta), where theta is the sweep angle.
Ok, if you have an airfoil with a certain section lift coefficient, does this mean that you have to use a higher lift coefficient to get the desired lift? Or is it the other way around?