Question

Is local induced change the angle of attack on a given section of a wing?

(a) True

(b) False

The question was posed to me in examination.

Question is from Prandtl’s Classical Lifting-Line Theory in portion Flow over Airfoils over Finite Wing of Aerodynamics

Answer 1

Correct option is (a) True

For explanation I would say: The local induced change of angle of attack on a given section can be quantified with the integral sum of the downwash induced by every other wing section. In turn, the integral sum of the lift on each down washed wing section is equal to the total desired amount of lift.