For a finite wing and an infinite wing (airfoil), zero lift angle of attack is zero.

For a finite wing and an infinite wing (airfoil), zero lift angle of attack is zero. Correct Answer True

When the lift is zero, there are no induced effects i.e. induced drag and induced angle of attack are zero. Also, since the induced angle of attack is zero, the geometric angle of attack is the same as the effective angle of attack. This means zero lift angle of attack is the same for wing and airfoil.
Bissoy MCQ

Related Questions

For a cambered airfoil section lift is 30N. Airfoil is operating in such way that dynamic lift is 20N. Determine the lift co-efficient for the airfoil.
If an airfoil is designed to provide lift curve slope as 7.8, then find airfoil efficiency. The actual lift curve slope of the airfoil is 7.4.
An airfoil is such that the drag produced by airfoil is 25N. Airfoil has chord of 2m and is experiencing dynamic pressure of 10Pa. Find the value of drag co-efficient for airfoil.
A symmetric airfoil is operating with flow velocity of 350m/s. The lift produced by the airfoil is 21 N at 0.008 rad AOA. If chord is c m then, what will be the pressure difference across the airfoil?
Flow separation causes lift to decrease with increasing angle of attack. This is inconsistent with the thin airfoil theory where the lift curve slope is 2π. This is a contradiction.
A NACA 22104 airfoil is operating at AOA = 3°. The lift-coefficient at this AOA is 0.15. Determine the value of angle of attack at designed lift co-efficient.
For a finite wing, the local airfoil section sees the angle of attack which is called as ____
A cambered airfoil is operating with 200N of lift. The velocity of the flow is 500m/s. Determine lift-induced drag by this camber airfoil.
I have to model a simple rectangular wing for my experimental aircraft testing a new technology on it. I have to choose an airfoil among the ten options given for my wing which would give the best aerodynamic performance. Suggest the best method to test and fix one airfoil.
When the lift becomes zero, the center of pressure of the cambered airfoil is at which point on the airfoil (consider given lengths are from the leading edge)?