Mission requirements
Propellant
Grain geometry
Simulation mode
Nozzle
Thermochemistry (CEA lookup)
- Formulation—
- Chamber temperature Tc— K
- Mean MW— g/mol
- Specific heat ratio γ—
- Characteristic velocity c*— m/s
- Density ρ— kg/m³
- Ideal Isp (SL opt, Pc=7 MPa)— s
Requirements check
Cross-section burn progress
Burn time— s
Peak Pc— MPa
Peak thrust— N
Total impulse— N·s
Initial Kn—
Propellant— g
Sliver— g
Isp— s