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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