According to thin airfoil theory, what is the location of the aerodynamic center x_{ac} from the leading edge as a fraction of the chord c for any thin cambered or symmetric airfoil?

Answer Key:

0.25

### Solution: Thin airfoil theory shows that for any thin 2D airfoil, the aerodynamic center (where pitching moment is independent of angle of attack) is located at the quarter chord point, x_{ac}/c = 0.25. Correct: 0.25.

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