Solid Rocket Motor Burn Rate & Pressure Calculator

Model propellant linear burn rate (Saint-Robert's Law), Kn area ratio, equilibrium chamber pressure, and combustion stability margins.

Solid Propellant Formulation Preset:

Burn Rate Coeff a (in/s / psi^n):

Pressure Exponent n: Must be strictly < 1.0 for stability

Propellant Density ρ_p (lb/in³):

Characteristic Velocity c* (ft/s):

Propellant Burning Area Ab (in²):

Nozzle Throat Diameter Dt (in):

Equilibrium Chamber Pressure (Pc):

—

— bar

Linear Propellant Burn Rate (r):

—

— mm/s

Area Ratio Kn (Ab / At):

—

Average Thrust (assuming CF=1.45):

—

Combustion Runaway Safety Margin:

—

Recommended Tools & Equipment

Tested hardware and components for high reliability

100% Free Tool Zero Sign-Up