The thrust equation relates the thrust produced by a propulsion system to the mass flow rate of the exhaust gases and their velocity. In SI (International System of Units) units, the thrust equation is typically expressed as
- is the thrust in Newtons (N).
- (pronounced “m-dot”) is the mass flow rate of the exhaust gases in kilograms per second (kg/s).
- is the exhaust velocity of the gases in meters per second (m/s).