For a symmetric airfoil, the lift coefficient for zero degree angle of attack is
(A) -1.0
(B) 0.0
(C) 0.5
(D) 1.0

Question ID - 156056 | SaraNextGen Top Answer

For a symmetric airfoil, the lift coefficient for zero degree angle of attack is
(A) -1.0
(B) 0.0
(C) 0.5
(D) 1.0