JoshTheEngineer | Explained: Maximum Thrust Nozzle Exit Pressure Condition @JoshTheEngineer | Uploaded December 2017 | Updated October 2024, 1 hour ago.
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 back-of-the-envelope 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 (RS-25).
===== RELEVANT BLOG POSTS =====
→ Turbojet Thrust Equation
joshtheengineer.com/2017/04/08/turbojet-thrust-equation
→ Quasi-1D Mass Conservation in Differential Form
joshtheengineer.com/2017/02/26/differential-form-quasi-1d-mass-conservation
===== RELEVANT VIDEOS =====
→ Converging-Diverging Nozzles
goo.gl/sqj2qu
→ Sonic State (Critical, Star)
goo.gl/qsDv3Y
→ Turbojet Thrust Equation Derivation
goo.gl/434UST
===== REFERENCES =====
►Gas Dynamics, Volume 1, Zucrow and Hoffman, ISBN-10: 047198440X
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 back-of-the-envelope 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 (RS-25).
===== RELEVANT BLOG POSTS =====
→ Turbojet Thrust Equation
joshtheengineer.com/2017/04/08/turbojet-thrust-equation
→ Quasi-1D Mass Conservation in Differential Form
joshtheengineer.com/2017/02/26/differential-form-quasi-1d-mass-conservation
===== RELEVANT VIDEOS =====
→ Converging-Diverging Nozzles
goo.gl/sqj2qu
→ Sonic State (Critical, Star)
goo.gl/qsDv3Y
→ Turbojet Thrust Equation Derivation
goo.gl/434UST
===== REFERENCES =====
►Gas Dynamics, Volume 1, Zucrow and Hoffman, ISBN-10: 047198440X
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