You are designing a wing with no aerodynamic twist based on the airfoil camber given by:...

 

 

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You are designing a wing with no aerodynamic twist based on the airfoil camber given by: N C 3.1 (H-H) = 0.1 The wing will have an aspect ratio of 10, a taper ratio of 0.8, and a constant geometric angle of attach of 5 degrees. Assume an induced lift slope factor of t = 0.01 and assume that the induced drag factor is NOT equal to the induced lift slope factor (8T). The density of air is 1.23 kg/m. Use both Thin Airfoil Theory and Prandtl's Lifting Line Theory to determine: (1) The smallest wing planform area needed to produce sufficient lift for take-off of a 40,000 kg airplane at a runway speed of 60 m/s. (2) The induced drag experienced by this wing during take-off. You are designing a wing with no aerodynamic twist based on the airfoil camber given by: N C 3.1 (H-H) = 0.1 The wing will have an aspect ratio of 10, a taper ratio of 0.8, and a constant geometric angle of attach of 5 degrees. Assume an induced lift slope factor of t = 0.01 and assume that the induced drag factor is NOT equal to the induced lift slope factor (8T). The density of air is 1.23 kg/m. Use both Thin Airfoil Theory and Prandtl's Lifting Line Theory to determine: (1) The smallest wing planform area needed to produce sufficient lift for take-off of a 40,000 kg airplane at a runway speed of 60 m/s. (2) The induced drag experienced by this wing during take-off.