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[B 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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