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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