Sections : Properties of the Atmosphere Aerofoil Section 2-D Geometry Joukowski Flow Mapping & Aerofoils 2-D Thin Aerofoil Theory 2-D Panel Methods 2-D Boundary Layer Modelling 3-D Lifting Line Theory 3-D Vortex Lattice Method Compressibility Corrections Prandtl Lifting Line SolutionsThis 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 ParametersWing span (b)(m)Wing root chord (cr)(m)Wing tip chord (ct)(m)Washout angle (Deg)Flap (- = Aileron) % spanAngle of Attack (Deg)Section DataWingRoot/Flap) dCL/dα (/rad)WingRoot/Flap) αo (Deg)WingTip/Aileron) dCL/dα (/rad)WingTip/Aileron) αo (Deg) Return to Prandtl Lifting Line page