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For Researchers · Airfoil & Wing Lab

Airfoil & Wing Lab for an energy audit

Built for researchers prototyping or validating an idea. Prototype fast, reproduce exactly, and share a citable, interactive version of your model. Simulate an energy audit live below — adjust the inputs and watch it respond, right in your browser.

Airfoil Polar

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Airfoil Lift & DragLive

the wing's polar

Controls

Presets

Angle of attack (°)

Aspect ratio

Lift rises almost linearly with angle of attack — until the airflow separates and the wing stalls, losing lift sharply. Drag has a fixed part plus induced drag that grows with lift squared and shrinks with aspect ratio. The lift-to-drag ratio, peaking at a modest angle, is the single number that governs a wing's efficiency.

▶ Run in Python

Data Inspector

Lift coeff. CL0.53

Drag coeff. CD0.033

Lift/Drag16.0

Statusattached

Governing equation

C_{D} = C_{D 0} + \frac{C _{L}^{2}}{π A R e} = 0.020 + \frac{0.5 3 ^{2}}{π \cdot 8 \cdot 0.85} = 0.033

Reading this result: Pre-stall: lift rises almost linearly with angle of attack at 6°, well below the ~15° stall angle. Adding camber would lift the entire curve higher.

Runs locally in your browser — free forever. Scale to the cloud when reality gets heavy.

↓

Fluid

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2D Fluid (CFD) StudioLive

Stam stable-fluids · Navier–Stokes

Controls

Speed1×

Click and drag on the canvas to inject dye and velocity.

Presets

Viscosity

Injection force

Dye amount

▶ Run in Python

Data Inspector

Grid96×96

Total dye0

Mean speed0.000

Max speed0.000

Enstrophy0.00e+0

Governing equation

\frac{\partial u}{\partial t} + (u \cdot \nabla) u = - \frac{\nabla p}{ρ} + 1.0 e - 7 \nabla^{2} u, \nabla \cdot u = 0

Reading this result: Near-zero viscosity: momentum barely dissipates, so vortices persist and the flow tips into turbulent, chaotic mixing.

Runs locally in your browser — free forever. Scale to the cloud when reality gets heavy.

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3D CFD

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3D CFD StudioLive

3D Stable Fluids · Navier–Stokes

Controls

Speed1×

A dye plume rises through a full 3D incompressible flow. Scrub the z-slice to inspect the volume.

Presets

z-slice

Plume force

▶ Run in Python

Data Inspector

Grid24³

Cells17,576

SchemeStam Stable Fluids

IncompressibleJacobi projection

Governing equation

\frac{\partial u}{\partial t} + (u \cdot \nabla) u = - \frac{\nabla p}{ρ} + ν \nabla^{2} u + f, \nabla \cdot u = 0, ∣ f ∣ = 30

Reading this result: At moderate force (30) the incompressible constraint is visible: each step the projection removes divergence, so fluid pushed up the center must fold back down along the sides.

Runs locally in your browser — free forever. Scale to the cloud when reality gets heavy.

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Also for:Students Educators Engineers Hobbyists & Makers K-12 Students First Responders General version →

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Frequently asked questions

Is this good for researchers?: Yes — this version of "Airfoil & Wing Lab for an energy audit" is framed for researchers prototyping or validating an idea. Prototype fast, reproduce exactly, and share a citable, interactive version of your model.
Do I need to install anything?: No. It runs in any modern browser, free, with no account required.