Rocket Propulsion
To understand this we must examine the basic thrust equation: F = q × Ve + (Pe Pa) × Ae where F = Thrust q = Propellant mass flow rate Ve = Velocity of exhaust gases Pe = Pressure at nozzle exit Pa = Ambient pressure Ae = Area of nozzle exit. The product qVe is called the momentum, or velocity, thrust and the product (PePa)Ae is called the ...