How can we get the maximum thrust from a nozzle? What exit pressure condition needs to met? In this video, we will go through a quick derivation showing that the ideal operating condition for a nozzle is when the exit pressure (at the exit plane of the nozzle) is equal to the pressure of the atmosphere that the nozzle is expanding into (also called the back pressure).

This result is pretty interesting when doing some quick backoftheenvelope calculations about different rocket nozzles, because we can deduce what their optimum operating altitude is. In one of my future videos, I'll be going through how to find the ideal operating altitude of the Space Shuttle Main Engine (RS25).

===== RELEVANT BLOG POSTS =====
→ Turbojet Thrust Equation
http://www.joshtheengineer.com/2017/0...

→ Quasi1D Mass Conservation in Differential Form
http://www.joshtheengineer.com/2017/0...

===== RELEVANT VIDEOS =====
→ ConvergingDiverging Nozzles
https://goo.gl/sqj2qu

→ Sonic State (Critical, Star)
https://goo.gl/qsDv3Y

→ Turbojet Thrust Equation Derivation
https://goo.gl/434UST

===== REFERENCES =====
►Gas Dynamics, Volume 1, Zucrow and Hoffman, ISBN10: 047198440X