Propellant consumption rate density Calculator

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)

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