For a symmetrical aerofoil, if the angle of attack is zero, CL is not zero. |
For an asymmetrical aerofoil, if the angle of attack is zero, CL is zero. |
For a symmetrical aerofoil, if the angle of attack is zero, CL is zero. |
For an asymmetrical aerofoil with positive camber, if the angle of attack is greater than zero, CL is zero. |
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