Question: Evaluate the lift coefficient at a = 5 deg for a thin aerofoil with camber line z (x)=0.1 (0.5 - 2) where 0 x
Evaluate the lift coefficient at a = 5 deg for a thin aerofoil with camber line z (x)=0.1 (0.5 - 2) where 0 x 1. Give your answer with two decimal places, e.g. 1.23. 1
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To evaluate the lift coefficient cl for a thin airfoil at an angle of attack alpha we can use the th... View full answer
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