Do I need to install anything?

No. It runs in any modern browser, free, with no account required.

For Educators · Nozzle & Jet

Nozzle & Jet for a net-zero home

Built for educators teaching it to a class. Drop a live demo into a lecture or assign it as a shareable link — no lab installs. Simulate a net-zero home live below — adjust the inputs and watch it respond, right in your browser.

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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Mach Cone

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Mach Cone & Sonic BoomLive

supersonic shock geometry

Controls

Presets

Mach number

Below the speed of sound, pressure waves race ahead of an aircraft. At and above Mach 1 the aircraft outruns its own sound, and the waves pile into a cone-shaped shock — the sonic boom. The faster it flies, the more sharply swept the Mach cone: its half-angle is arcsin(1/M). This geometry governs supersonic and hypersonic vehicle design.

▶ Run in Python

Data Inspector

Mach2.0

Regimesupersonic

Cone half-angle30.0°

Governing equation

μ = arcsin \frac{1}{M} = arcsin \frac{a}{v} = arcsin \frac{1}{2.0} = 30. 0^{\circ}

Reading this result: At Mach 2.0 the half-angle is arcsin(1/M) = 30.0° — faster flight sweeps the Mach cone tighter around the flight path.

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

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Rocket

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Rocket Equation (Tsiolkovsky)Live

Δv = g·Isp·ln(m₀/m_f)

Delta-v budget

5524 m/s

LEO (Earth orbit)

59%

Moon transfer

44%

Mars transfer

42%

Escape Earth

49%

Controls

The equation that rules spaceflight. Your Δv budget depends only on exhaust velocity and the ratio of full-to-empty mass — and it's brutally logarithmic.

Presets

Wet mass m₀ (t)

Dry mass m_f (t)

Specific impulse Isp (s)

▶ Run in Python

Data Inspector

Δv5524 m/s

Mass ratio5.00

Propellant400 t

Exhaust vel.3432 m/s

Governing equation

Δ v = v_{e} ln \frac{m _{0}}{m _{f}} = 3432 ln \frac{500}{100} = 5524 m/s

Reading this result: At 5524 m/s this stage cannot reach orbit; since Δv grows only with the log of mass ratio, big gains need a much emptier tank or higher Isp.

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

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

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Frequently asked questions

Is this good for educators?: Yes — this version of "Nozzle & Jet for a net-zero home" is framed for educators teaching it to a class. Drop a live demo into a lecture or assign it as a shareable link — no lab installs.
Do I need to install anything?: No. It runs in any modern browser, free, with no account required.