Uploaded March 2017 | Updated September 2026, 2 weeks ago
What are afterburners, and how do they work? In this video, I'll go into some detail on how different parts of the afterburner work, and why they are designed that way.
===== NOTES =====
► I always speak pretty quickly in my videos, so if you need to take it slower, you have the option of slowing down the video speed to 0.75x or even 0.5x the normal speed (I realize that I speak particularly fast in this video).
► Apparently since YouTube got rid of annotations, I have no way of letting you know in the video that I made a mistake, so I'll just have to hope that you read my video descriptions.
► At around 4:49, I say that "droplet evaporation times are higher for higher temperatures". I meant to say that droplet evaporation times are higher for LOWER temperatures, which is why the cold bypass flow takes longer to evaporate droplets. Another way of saying this is that for the same droplet diameter, it will take longer to evaporate in a colder flow than in a hotter flow.
===== RELEVANT VIDEOS =====
→ In a Nutshell: Afterburners
goo.gl/fCxCqs
→ Area-Mach Number Relation
goo.gl/yNuu2t
===== REFERENCES =====
► "Afterburners" in The Aerothermodynamics of Aircraft Gas Turbine Engines, Zukoski
► Mechanics and Thermodynamics of Propulsion, Hill and Peterson
► Aerothermodynamics of Gas Turbine and Rocket Propulsion, Oates
► Aircraft Propulsion, Farokhi
► Aerospace Propulsion Systems, Ward
► Fundamentals of Jet Propulsion with Applications, Flack
===== THUMBNAIL PHOTO CREDIT =====
By United States Navy, Mass Communications Specialist 2nd Class Michael D. Cole [Public domain], via Wikimedia Commons
What are afterburners, and how do they work? In this video, I'll go into some detail on how different parts of the afterburner work, and why they are designed that way.
===== NOTES =====
► I always speak pretty quickly in my videos, so if you need to take it slower, you have the option of slowing down the video speed to 0.75x or even 0.5x the normal speed (I realize that I speak particularly fast in this video).
► Apparently since YouTube got rid of annotations, I have no way of letting you know in the video that I made a mistake, so I'll just have to hope that you read my video descriptions.
► At around 4:49, I say that "droplet evaporation times are higher for higher temperatures". I meant to say that droplet evaporation times are higher for LOWER temperatures, which is why the cold bypass flow takes longer to evaporate droplets. Another way of saying this is that for the same droplet diameter, it will take longer to evaporate in a colder flow than in a hotter flow.
===== RELEVANT VIDEOS =====
→ In a Nutshell: Afterburners
goo.gl/fCxCqs
→ Area-Mach Number Relation
goo.gl/yNuu2t
===== REFERENCES =====
► "Afterburners" in The Aerothermodynamics of Aircraft Gas Turbine Engines, Zukoski
► Mechanics and Thermodynamics of Propulsion, Hill and Peterson
► Aerothermodynamics of Gas Turbine and Rocket Propulsion, Oates
► Aircraft Propulsion, Farokhi
► Aerospace Propulsion Systems, Ward
► Fundamentals of Jet Propulsion with Applications, Flack
===== THUMBNAIL PHOTO CREDIT =====
By United States Navy, Mass Communications Specialist 2nd Class Michael D. Cole [Public domain], via Wikimedia Commons

![Explained: Normal Vector [CFD]
This is a video describing the general technique of finding a vector normal to another vector, with an emphasis on its relation to CFD codes. Explained: Normal Vector [CFD]](https://i.ytimg.com/vi/mixm2y8ukTg/mqdefault.jpg)
![Explained: Line And Scatter Plot [Excel]
This video explains how to display both line data and scatter data on the same plot in Excel. Explained: Line And Scatter Plot [Excel]](https://i.ytimg.com/vi/nFylutP84ro/mqdefault.jpg)



![Explained: Converging-Diverging Nozzle
Why do rocket engines look the way they do? In this video, Ill be explaining what a converging-diverging (CD) nozzle is, and how the flow changes as it passes through it.
See the Relevant Videos section below for some more in-depth videos on each of the flow states, including examples!
NOTES
► At 11:28, I say so far, we have subsonic flow throughout the nozzle for all these cases. I meant to say that we have isentropic flow throughout the nozzle for all these cases.
RELEVANT VIDEOS
Pressure Ratio Delineations
https://goo.gl/VQnH1n
Normal Shock in the Nozzle Calculations
https://www.youtube.com/watch?v=b0wvwkKqoVw
Overexpanded Flow Calculations
Coming soon!
Underexpanded Flow Calculations
Coming soon!
Area-Mach Number Relation
https://goo.gl/j4FwQX
Sonic State (Critical, Star)
https://goo.gl/vhjESy
Normal Shock Relations
https://goo.gl/bhw6Ln
Isentropic Relations
https://goo.gl/mkdNHd
Stagnation Relations
https://goo.gl/hBY2AV
RELEVANT BLOG POST
http://www.joshtheengineer.com/2016/11/16/solving-the-area-mach-number-relation/
REFERENCES
► Notes by Matt MacLean
► Modern Compressible Flow, Anderson
Amazon Link: https://goo.gl/9B7F8H
► Elements of Gasdynamics, Liepmann and Roshko
Amazon Link: https://goo.gl/brfScu
► Gas Dynamics, Zucrow and Hoffman
Amazon Link: https://goo.gl/mwLk8L
THUMBNAIL IMAGE
By NASA (NIX #: MSFC-0201422. [1], Alt. URL.) [Public domain], via Wikimedia Commons Explained: Converging-Diverging Nozzle](https://i.ytimg.com/vi/p8e8A3sdVOg/mqdefault.jpg)

![Explained: Normal Shock Relations
In this video we will go through the full derivation of the normal shock relations. We will solve for downstream Mach number (M2), velocity ratio (u2/u1), density ratio (rho2/rho1), pressure ratio (P2/P1), and temperature ratio (T2/T1). We will assume the gas is calorically perfect (i.e. the specific heats are constant), which allows us to solve for all these values as only a function of specific heat ratio (gamma) and the upstream Mach number (M1).
ERRORS
► For the board from 9:09 - 10:33, the terms in brackets on the top line are correct, but the terms in brackets on the next two lines are incorrect (I switched a negative sign with a positive sign). When I bring the expression over to the next board at 10:34, the bracketed term is back to being correct, with a negative sign instead of the positive sign. [Thank you Pratheesh Prabhakar]
► From 21:44 to the end of the video, the second bracketed term in the final T2/T1 equation should be inverted (i.e, I have written it there as rho2/rho1, where it should really be rho1/rho2 as mentioned on the line above). [Thank you Pratheesh Prabhakar and Osama Hamdy]
RELEVANT VIDEOS
→ 1D Mass Eqn
https://goo.gl/0vesye
→ 1D Momentum Eqn
https://goo.gl/FHFUi4
→ 1D Energy Eqn
https://goo.gl/RSXVyc
→ Thermally Perfect Gas
https://goo.gl/maElnm
→ Specific Heats
https://goo.gl/kdf1B7
→ Isentropic Relations
https://goo.gl/Q8Rv9O
REFERENCES
► Notes by Matt MacLean
► Modern Compressible Flow, Anderson
► Elements of Gasdynamics, Liepmann and Roshko
► Gas Dynamics, Zucrow and Hoffman Explained: Normal Shock Relations](https://i.ytimg.com/vi/pR7mWvDWEJY/mqdefault.jpg)

![Explained: Hydrogen Burnoff Igniters [Space Shuttle]
What are the sparks seen beneath the space shuttles main engines just before launch? These sparks come from the hydrogen burnoff system that makes sure there is no excess hydrogen near the engines before ignition.
The sparks from the igniters can be seen in the video below at 1:09.
http://www.youtube.com/watch?v=T7vGqQUhciE Explained: Hydrogen Burnoff Igniters [Space Shuttle]](https://i.ytimg.com/vi/pahefmotTNk/mqdefault.jpg)