Evaluate the lift coefficient at a = 5 deg for a thin aerofoil with camber line...

Transcribed Image Text:

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 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

Answer rating: 100% (QA)

To evaluate the lift coefficient cl for a thin airfoil at an angle of attack alpha we can use the th... View the full answer