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.
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.