Consider the wing planform shown in figure Q3. It is an unswept wing of span b = 12m and root chord cs = at = 0.5, and outer portion linear taper profile from 2 Ct = 1m. The wing has constant aerofoil section with lift curve slope ko 27 per radian and has a drag bucket profile drag coefficient 0.002. Wing performance is to be estimated from lifting line theory limiting the calculation to the first two non-zero A coefficients. i) Calculate the wing lift curve slope. ii) For the untwisted wing calculate the wing drag polar in the form Cp Cpo + KC. %3D 1.6m with inner portion linear taper profile down to chord length c = = 1.2m 0.5 to the tip with tip chord %3D %3D %3D

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