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Assuming elliptical lift distribution and a rectangular wing with span of 11.5m, find the ratio of C (Overall wing) to cl (aerofoil section) at

Assuming elliptical lift distribution and a rectangular wing with span of 11.5m, find the ratio of C (Overall

Assuming elliptical lift distribution and a rectangular wing with span of 11.5m, find the ratio of C (Overall wing) to cl (aerofoil section) at a spanwise L position 0.32 measured as a fraction of the overall semi-span from the centre. Take I to be 59, give your answer to 2dp: 0

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Solution To find the ratio of C to cl we need to use the lift distribution equation for an elliptical lift distribution L 12 C R2 S 1 RS212 where L li... blur-text-image

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