Uploaded August 2019 | Updated September 2026, 2 weeks ago
This is the simplest of the elementary potential flows. We will start with an arbitrary freestream velocity, derive the velocity potential, and then verify the original velocity. Using the Cartesian velocity X and Y components, we will code up a simple script for the flow-field in a uniform flow, and compute the circulation around an arbitrary curve.
==== RELEVANT VIDEOS ====
Incompressible Potential Flow
- youtube.com/watch?v=Zo5XIcX8s2Q
Source/Sink Flow
- youtube.com/watch?v=eLDI_jV3yo0
Uniform + Source/Sink Flow
- youtube.com/watch?v=zIvpN9f9dAA
Vortex Flow
- youtube.com/watch?v=61jvr3rtmLE
Uniform + Vortex Flow
- youtube.com/watch?v=SoMuRp5v16w
==== RELEVANT LINKS ====
Blog post about incompressible potential flow
► joshtheengineer.com/2019/05/05/introduction-to-incompressible-potential-flow
Blog and code for uniform flow
► joshtheengineer.com/2019/08/25/elementary-flow-uniform-flow
GitHub: Panel Methods
► github.com/jte0419/Panel_Methods
===== REFERENCES =====
Note: the links are Amazon affiliate links. If you do happen to want to buy the book and use the link below, it helps me out a little.
► Fundamentals of Aerodynamics, Anderson
amzn.to/3emVuXU
► Foundations of Aerodynamics, Kuethe and Chow
amzn.to/2yMg1Vi
► Theory of Wing Sections, Abbott and Doenhoff
amzn.to/2wvZyUt
► Fundamental Mechanics of Fluids, Currie
amzn.to/2RpX2q4
► Elements of Gasdynamics, Liepmann and Roshko
amzn.to/2XrZjoo
This is the simplest of the elementary potential flows. We will start with an arbitrary freestream velocity, derive the velocity potential, and then verify the original velocity. Using the Cartesian velocity X and Y components, we will code up a simple script for the flow-field in a uniform flow, and compute the circulation around an arbitrary curve.
==== RELEVANT VIDEOS ====
Incompressible Potential Flow
- youtube.com/watch?v=Zo5XIcX8s2Q
Source/Sink Flow
- youtube.com/watch?v=eLDI_jV3yo0
Uniform + Source/Sink Flow
- youtube.com/watch?v=zIvpN9f9dAA
Vortex Flow
- youtube.com/watch?v=61jvr3rtmLE
Uniform + Vortex Flow
- youtube.com/watch?v=SoMuRp5v16w
==== RELEVANT LINKS ====
Blog post about incompressible potential flow
► joshtheengineer.com/2019/05/05/introduction-to-incompressible-potential-flow
Blog and code for uniform flow
► joshtheengineer.com/2019/08/25/elementary-flow-uniform-flow
GitHub: Panel Methods
► github.com/jte0419/Panel_Methods
===== REFERENCES =====
Note: the links are Amazon affiliate links. If you do happen to want to buy the book and use the link below, it helps me out a little.
► Fundamentals of Aerodynamics, Anderson
amzn.to/3emVuXU
► Foundations of Aerodynamics, Kuethe and Chow
amzn.to/2yMg1Vi
► Theory of Wing Sections, Abbott and Doenhoff
amzn.to/2wvZyUt
► Fundamental Mechanics of Fluids, Currie
amzn.to/2RpX2q4
► Elements of Gasdynamics, Liepmann and Roshko
amzn.to/2XrZjoo
![Explained: Sonic State (Critical, Star)
Heres the next video in our quest to understand jet engine and rocket nozzles (among other things). We will be talking about the sonic state, which is also called the critical state or the star state.
These values are useful for determining whether flow through a nozzle is choked. If the nozzle is indeed choked, then the sonic state values (P*, rho*, T*, etc.) are the actual static quantities at the throat of the nozzle.
RELEVANT VIDEOS
→ Stagnation Relations
https://goo.gl/FMFUBA
→ Area-Mach Number Relation
https://goo.gl/Hp6uGQ
REFERENCES
► Notes by Matt MacLean
► Modern Compressible Flow, Anderson
► Elements of Gasdynamics, Liepmann and Roshko
► Gas Dynamics, Zucrow and Hoffman
THUMBNAIL
By Ad Meskens (Own work) [Attribution, GFDL (http://www.gnu.org/copyleft/fdl.html) or CC BY-SA 4.0-3.0-2.5-2.0-1.0 (http://creativecommons.org/licenses/by-sa/4.0-3.0-2.5-2.0-1.0)], via Wikimedia Commons Explained: Sonic State (Critical, Star)](https://i.ytimg.com/vi/jnRudznUqDM/mqdefault.jpg)
![Explained: Waitbar [MATLAB]
A waitbar (or progress bar) allows you to visualize when a program will finish. The argument to the waitbar fills up the bar with the percentage specified. While its a fun way to see how long you have to wait until everything is done computing, it is extremely time consuming, and I would probably recommend just outputting data to the command window using fprintf. Explained: Waitbar [MATLAB]](https://i.ytimg.com/vi/k2wKPxRUPiE/mqdefault.jpg)


![Explained: NACA 4-Digit GUI Part 10/10 [MATLAB]
This is the last video in my 10-video series on coding a program in MATLAB to compute, display, and save a NACA 4-digit airfoil.
IN THIS VIDEO:
We add in the code for saving the airfoil data out to a text file. Both the LE to TE and TE to LE methods are coded. A comparison between the output from this code and the data from the UIUC airfoil data site (see link below) is made to confirm that our code works the way it should.
UIUC Airfoil Data Site:
http://m-selig.ae.illinois.edu/ads/coord_database.html
IN THIS SERIES:
Part 1/10 : https://goo.gl/9UBgbo
Part 2/10 : https://goo.gl/jRRcYJ
Part 3/10 : https://goo.gl/rSVLHo
Part 4/10 : https://goo.gl/HwHB39
Part 5/10 : https://goo.gl/AlDne8
Part 6/10 : https://goo.gl/7n1QP7
Part 7/10 : https://goo.gl/nTGleR
Part 8/10 : https://goo.gl/ez247P
Part 9/10 : https://goo.gl/8mXYcc
Part 10/10: https://goo.gl/ovBlbW
If youve made it this far, thanks for watching! I hope you enjoyed it. Let me know if you have any questions or comments. Explained: NACA 4-Digit GUI Part 10/10 [MATLAB]](https://i.ytimg.com/vi/kk-5MShSTwA/mqdefault.jpg)


![Explained: Afterburners
What are afterburners, and how do they work? In this video, Ill 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 Ill 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
https://goo.gl/fCxCqs
→ Area-Mach Number Relation
https://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: Afterburners](https://i.ytimg.com/vi/mH3BBUpzj9c/mqdefault.jpg)

![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)