Question
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 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...Get Instant Access to Expert-Tailored Solutions
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Physical Chemistry
Authors: Thomas Engel, Philip Reid
3rd edition
805338423, 080533842X, 978-0321812001
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