De Laval Supersonic Nozzle Flow Calculator
Compute sonic throat conditions ($M=1$), choked mass flow rate ($\dot{m}$), exit Mach number ($M_e$), expansion area ratio ($A_e/A^*$), and ideal thrust.
Chamber & Nozzle Parameters
Combustion gas ~1.22-1.30, Air=1.40
Air=287, Rocket gas ~320-380
Supersonic Expansion Performance
Exit Mach Number (M_e)
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Supersonic Exit Velocity
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Area Ratio A_e/A*
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Choked Mass Flow
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Design Thrust F
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Nozzle Aerodynamics Summary
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