if you’re looking for the cross-sectional area of an aircraft engine’s exhaust nozzle, which is related to thrust, it can be calculated based on the nozzle diameter. The formula for the cross-sectional area A of a circular nozzle 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 Thrust (in square meters, m²).
- V is the velocity of the Thrust (in meters per second, m/s).