- All Calculation Types
- O/F Ratio
- Fuel Percent
- Equivalence Ratio
- Phi
- Pressure
- Temperature
- Density
- Enthalpy
- Internal Energy
- Gibbs Free Energy
- Entropy
- Compressibility*
- Molecular Weight
- Heat Capacity*
- Heat Capacity (Gas)*
- Gamma (Gas)
- Gamma
- Speed of Sound
- Molecular Weight (Mix)
- Viscosity
- Specific Heat (Equilibrium & Frozen)*
- Conductivity (Equilibrium & Frozen)
- Prandtl (Equilibrium & Frozen)
- Mass or Mole Product Fraction
- Rocket Calculation Type
- Injector pressure ratio
- Chamber pressure ratio
- Mach Number
- Nozzle Area Ratio
- C* efficiency
- Thrust Coefficient
- Vacuum Isp
- Isp at Given Pressure
- Isp at Altitude
- Density Isp
- Detonation Calculation Type
- Final Pressure
- Final Temperature
- Final Enthalpy
- Final Mach Number
- Final Gamma
- Final Speed of Sound
- Pressure Ratio
- Temperature Ratio
- Mach Ratio
- Density Ratio
- Final Mach Number
- Final Speed of Sound
- Shock Calculation Type
- Initial Pressure
- Initial Temperature
- Initial Density
- Initial Enthalpy
- Initial Internal Energy
- Initial Gibbs Free Energy
- Initial Entropy
- Initial Compressibility
- Initial Molecular Weight (Mix)
- Initial Heat Capacity
- Initial Gamma
- Initial Speed of Sound
- Initial Mach Number
- Initial Velocity
- Final Mach Number
- Final Velocity
- Pressure Ratio
- Temperature Ratio
- Mach Ratio
- Density Ratio
- Velocity Difference
- Oblique Incident Flow Angle
- Oblique Shock Wave Angle
*Cequel includes a Lennard-Jones potential compressibility model
*Heat Capacity = Heat capacity for reacting flows as function of temperature
*Heat Capacity (Gas) = Heat capacity for non-reacting (frozen) flows as function of temperature
*Specific Heat (Equilibrium) = Heat capacity for reacting flows. Only includes data from gases with known transport properties, and does not include effect of condensed species. Should be very close in value to CP