Find location of aerodynamic centre from leading edge if, chord is 10m and airfoil has flow velocity of 0.2 M.

0.2 m

2.5 m

5 m

10 m

Correct Answer : 2.5 m

Explanation : Given, velocity = 0.2M = 0.2*340 = 68m/s
Chord = 10m
Given velocity is less than the sonic speed.
Hence, location of aerodynamic center is = 25% of chord = 0.25*10 = 2.5m from leading edge.

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