What is the Airfoil & Wing Lab multi-solver?

Airfoil & Wing Lab is a guided workflow that chains 3 individual PolySim solvers into one end-to-end analysis, piping each result into the next step.

Yes. Every step runs entirely in your browser using real numerics — no install, no account, no cloud cost. Custom or private solver packs are available as a paid service.

Fluids & Energy Pack · Multi-Solver

Airfoil & Wing Lab

Lift, drag, flow. This multi-solver chains 3 solvers into a single guided workflow — run each step in order and carry the result forward.

Workflow steps

or unlock everything with Pro →

Airfoil Polar

open full solver →

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

open full solver →

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.

↓

3D CFD

open full solver →

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.

Need a private, branded version?

We build custom solvers and workflows for labs, firms, agencies, and courses — your parameters, your branding, your data.

Explore Custom Solver Sets →

More in the Fluids & Energy pack

Pump & Piping System HVAC Duct Designer Wind Turbine Yield Heat Exchanger Sizing Nozzle & Jet Compressor Map Pipeline Network Cooling Fan Selection

Frequently asked questions

What is the Airfoil & Wing Lab multi-solver?: Airfoil & Wing Lab is a guided workflow that chains 3 individual PolySim solvers into one end-to-end analysis, piping each result into the next step.
Is it free to use?: Yes. Every step runs entirely in your browser using real numerics — no install, no account, no cloud cost. Custom or private solver packs are available as a paid service.