Rocket Characteristic Velocity (c*) Calculator

Calculate theoretical and delivered characteristic exhaust velocity (c*), combustion efficiency, chamber temperature, and required throat area.

Propellant Combination Preset:

Chamber Flame Temp Tc (K):

Mean Molecular Weight Mw (g/mol):

Specific Heat Ratio γ:

Combustion Efficiency η_c* (%): Typical modern injector: 95-98%

Chamber Pressure Pc (bar):

Total Mass Flow Rate m_dot (kg/s):

Delivered c* Velocity:

—

— ft/s

Theoretical Ideal c*:

—

η = — %

Required Throat Area (At):

—

— in²

Throat Diameter (Dt):

—

— in

Injector Combustion Quality:

—

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