I need to find the angle of attack for CL=.40 and also lift coefficient distributions,induced angle of attack distributions and induced drag coefficients for two aspect ratios 6 and 12 for untwisted uncambered rectangular wings.
Also, for the rectangular wing find the same.
I want it in One day
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Hello, I have a master degree in aerospace. Please do share complete description of the problem. and Expected results I suppose Prandtl's lifing line theory can be used to solve such a problem.