Aerofoil and wing

Lift, pitching moment and the pressure on any NACA section or your own coordinates, with the flow round it drawn live — then the boundary layer, the drag polar and the finite wing in 3D.

FREE · NO SIGN-UP v1.0.0 · verified against 9 reference cases

INPUTSI · standard atmosphere

1 · Section

Start from NACA designation four or five digits

Angle of attack [°]

2 · Flow Set by

Air speed [m/s] Chord [m] the root chord of the wing

Altitude [m] standard atmosphere, 0 to 20 000 m

3 · Boundary layer Pro+

Trip, upper [x/c] empty: free transition Trip, lower [x/c] empty: free transition

Polar from [°] Polar to [°]

4 · Wing Pro+

Span [m] Taper ratio tip / root chord

Tip twist [°] negative: washout

Example values, not a real aircraft. Low speed: incompressible flow, Mach below about 0.3.

LIFT COEFFICIENT0.744

FLOW · LIVE

PRESSURE COEFFICIENT

LIFT CURVE

DRAG POLARPro+

WING · 3D · LIFTING LINEPro+

SPANWISE LOADINGPro+

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HOW IT'S CALCULATED · WITH YOUR NUMBERS

Step by step, with your numbers

01
Equilibrium████ ██ ███████ · ██████ = ██.██
02
Reactions████ ██ ███████ · ██████ = ██.██
03
Shear force████ ██ ███████ · ██████ = ██.██
04
Bending moment████ ██ ███████ · ██████ = ██.██
05
Deflection████ ██ ███████ · ██████ = ██.██
06
Stress████ ██ ███████ · ██████ = ██.██

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References: Abbott & von Doenhoff, Theory of Wing Sections (1959) — section geometry, Theodorsen velocity distributions and wind-tunnel data; Katz & Plotkin, Low-Speed Aerodynamics — vortex panels; Thwaites, Michel and Head boundary-layer methods; Glauert's lifting line; ICAO standard atmosphere. Checked against XFOIL 6.99 and the AeroSandbox vortex-lattice method.

ASSUMPTIONS & LIMITS

Incompressible, steady, two-dimensional flow round the section; Mach number below about 0.3.
The International Standard Atmosphere (ICAO) for the air at the altitude given, Sutherland's law for its viscosity.
Inviscid section: a vortex panel method with 120 panels and the Kutta condition. The flow picture is the inviscid flow; the wake and the boundary layer are not drawn.
Viscous section (Pro+): integral boundary layer coupled to the panel solution by source panels (the displacement effect), transition by Michel's criterion or a trip, profile drag by Squire–Young. Laminar separation bubbles, trailing-edge stall and c_l,max are not modelled.
Wing (Pro+): Prandtl's lifting line, straight unswept wing, symmetric loading, no fuselage or wall effect; section properties from the viscous solution at α = 0° and 4°.

DISCLAIMER · For education and preliminary sizing only. Results must be reviewed by a qualified engineer before use in design.

BEYOND THE LIFTING LINE

Stall, flaps and slats, swept wings, compressibility, propeller and fuselage interference — we model the complete aircraft or rotor with CFD.

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