Is this good for hobbyists & makers?

Yes — this version of "Compressible Nozzle Flow for a rocket ascent" is framed for hobbyists & makers exploring it for fun. Play with real physics and math, no license and no setup — just open and tinker.

Do I need to install anything?

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

For Hobbyists & Makers · Compressible Nozzle Flow

Compressible Nozzle Flow for a rocket ascent

Built for hobbyists & makers exploring it for fun. Play with real physics and math, no license and no setup — just open and tinker. Simulate a rocket ascent live below — adjust the inputs and watch it respond, right in your browser.

Compressible Nozzle FlowLive

converging–diverging & choked flow

Controls

Presets

Specific-heat ratio γ

Back/stagnation pressure ratio

In a converging–diverging (de Laval) nozzle, gas accelerates to Mach 1 at the throat, then goes supersonic in the diverging section. The exit Mach number follows from the pressure ratio via isentropic flow relations. Educational tool.

▶ Run in Python

Data Inspector

Exit Mach number1.71

Area ratio Aₑ/A*1.35

Flow regimesupersonic

Governing equation

\frac{A _{e}}{A ^{*}} = \frac{1}{1.71} [\frac{2}{1.4 + 1} (1 + \frac{1.4 - 1}{2} 1.7 1^{2})]^{\frac{1.4 + 1}{2 ( 1.4 - 1 )}} = 1.35

Reading this result: Exit Mach 1.71 is supersonic — the flow chokes at Mach 1 in the throat, then the diverging section keeps accelerating it, which demands an area ratio Ae/A* of 1.35.

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Frequently asked questions

Is this good for hobbyists & makers?: Yes — this version of "Compressible Nozzle Flow for a rocket ascent" is framed for hobbyists & makers exploring it for fun. Play with real physics and math, no license and no setup — just open and tinker.
Do I need to install anything?: No. It runs in any modern browser, free, with no account required.