Question 6 (20 marks) A cascade of aerofoils, which has a blade solidity of 1.5, results in the following data: a-50, a,-20, inlet relative air velocity-24 m/s, and the pressure loss is 15 Pa. Take the density of the air to be 1.2 kg/m (1) Draw the inlet and outlet velocity triangles in the figure below (2) Mark the blade angle in the figure below (5 marks) (5 marks) (3) Determine CL and Cp. (10 marks) Possible equations that you may use 2T PR Sin (Cot END
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