The propellant consumption rate density formula, often denoted as Ë™, is typically expressed as the mass flow rate of propellant divided by the cross-sectional area of the exhaust nozzle. Mathematically, it can be represented as:
Where:
- Ë™ is the propellant consumption rate density (kg/s)
- is the thrust force (N)
- is the cross-sectional area of the exhaust nozzle (m²)