Request to add adjusted drag model to induced_drag_aircraft.py

[danielenriquez59]

Currently induced_drag is calculated via the standard induced drag equation:

CDi = k*CL^2

there should be an option to utilize the adjusted drag model:
CDi = k*(CL-CL0)^2

as it can affect drag predictions significantly.

Maybe make an try statement:

       try : 
            cdi_v_wing = K*cdp_wing*(cl_wing - wing.cl0)**2 #adjusted drag model
        except :
            cdi_v_wing = K*cdp_wing*(cl_wing**2)