The mass-specific impulse (Isp) formula is typically used in the context of rocket propulsion and is calculated as the total impulse divided by the propellant mass expended. Mathematically, it’s represented as:
Where:
- is the mass-specific impulse (usually measured in seconds),
- is the thrust generated by the rocket (measured in newtons),
- is the duration of the rocket burn (measured in seconds),
- is the mass of propellant expended during the burn (measured in kilograms).