One of the important variables in determining how much thrust a rocket can produce is the mass flow rate. In this video, we will derive an expression for the mass flow rate through a converging or converging diverging nozzle.

===== NOTES =====
► This expression only works when the flow is choked. For a convergingdiverging (CD) nozzle, the flow should always be choked (although you still need to check). A little more care is needed when using the expression for a converging nozzle, because a lot of converging nozzles operate under conditions where they are not necessarily choked.

===== RELEVANT VIDEOS =====
→ Rocketdyne F1 Mass Flow Rate Example
https://goo.gl/Ezp54H

→ ConvergingDiverging Nozzle
https://goo.gl/jrsyoJ

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

→ AreaMach Number Relation [CPG]
https://goo.gl/j4FwQX

===== REFERENCES =====
► Notes by Matt MacLean
► Modern Compressible Flow, Anderson
► Elements of Gasdynamics, Liepmann and Roshko
► Gas Dynamics, Zucrow and Hoffman

===== THUMBNAIL IMAGE =====
By NASA (NASA Human Space Flight Gallery (image link)) [Public domain], via Wikimedia Commons