<P> The thrust to weight ratio of rockets typically greatly exceeds that of airbreathing jet engines because the comparatively far greater density of rocket fuel eliminates the need for much engineering materials to pressurize it . </P> <P> Many factors affect a thrust - to - weight ratio . The instantaneous value typically varies over the flight with the variations of thrust due to speed and altitude along with the weight due to the remaining propellant and payload mass . The main factors include freestream air temperature, pressure, density, and composition . Depending on the engine or vehicle under consideration, the actual performance will often be affected by buoyancy and local gravitational field strength . </P> <P> The Russian - made RD - 180 rocket engine (which powers Lockheed Martin's Atlas V) produces 3,820 kN of sea - level thrust and has a dry mass of 5,307 kg . Using the Earth surface gravitational field strength of 9.807 m / s2, the sea - level thrust - to - weight ratio is computed as follows: (1 kN = 1000 N = 100 kg ⋅ m / s2) </P> <Dl> <Dd> T W = 3, 820 k N (5, 307 k g) (9.807 m / s 2) = 0.07340 k N N = 73.40 N N = 73.40 (\ displaystyle (\ frac (T) (W)) = (\ frac (3,820 \ \ mathrm (kN)) ((5,307 \ \ mathrm (kg)) (9.807 \ \ mathrm (m / s ^ (2))))) = 0.07340 \ (\ frac (\ mathrm (kN)) (\ mathrm (N))) = 73.40 \ (\ frac (\ mathrm (N)) (\ mathrm (N))) = 73.40) </Dd> </Dl>

How many newtons does a jet engine produce