The mass flow rate of thrust, in the context of aircraft design, refers to the rate at which mass is ejected from the aircraft’s engines to produce thrust. This is a crucial parameter in understanding an aircraft’s propulsion system. The formula to calculate the mass flow rate of thrust is:
- ṁ is the mass flow rate in kilograms per second (kg/s).
- ρ is the air density in kilograms per cubic meter (kg/m³).
- A is the cross-sectional area Thurst (in square meters, m²).
- V is the velocity of the Fuel Thrust (in meters per second, m/s).