Prandtl Lifting Line Solutions This form calculates the lift distribution, downwash and total lift and induced drag of a simple unswept wing. The geometry of the wing can be entered along with its aerofoil section properties.
Input Parameters Wing span (b)(m) Wing root chord (cr)(m) Wing tip chord (ct)(m) Washout angle (Deg) Flap (- = Aileron) % span Angle of Attack (Deg) Section Data WingRoot/Flap) dCL/dα (/rad) WingRoot/Flap) αo (Deg) WingTip/Aileron) dCL/dα (/rad) WingTip/Aileron) αo (Deg)

 

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