Uploaded August 2019 | Updated September 2026, 2 weeks ago
This is the last of the elementary flow videos, and here we will combine uniform flow with vortex flow. After showing the Cartesian velocity components on the board, we will go through a script to compute the combined flow-field and calculate the circulation around some arbitrary curves.
==== RELEVANT VIDEOS ====
Incompressible Potential Flow
- youtube.com/watch?v=Zo5XIcX8s2Q
Uniform Flow
- youtube.com/watch?v=jCTTDclJZEk
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
==== RELEVANT LINKS ====
Blog post about incompressible potential flow
► joshtheengineer.com/2019/05/05/introduction-to-incompressible-potential-flow
Blog and code for combined uniform and vortex flow
► joshtheengineer.com/2019/08/25/combined-flow-uniform-and-vortex-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 last of the elementary flow videos, and here we will combine uniform flow with vortex flow. After showing the Cartesian velocity components on the board, we will go through a script to compute the combined flow-field and calculate the circulation around some arbitrary curves.
==== RELEVANT VIDEOS ====
Incompressible Potential Flow
- youtube.com/watch?v=Zo5XIcX8s2Q
Uniform Flow
- youtube.com/watch?v=jCTTDclJZEk
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
==== RELEVANT LINKS ====
Blog post about incompressible potential flow
► joshtheengineer.com/2019/05/05/introduction-to-incompressible-potential-flow
Blog and code for combined uniform and vortex flow
► joshtheengineer.com/2019/08/25/combined-flow-uniform-and-vortex-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
![Streamline Geometric Integral VPM [Nx(pj) and Ny(pj)]
In this video, we go through the X and Y velocity expression geometric integrals for the vortex panel method. This is the last geometric integral derivation we will need.
RELEVANT VIDEOS
► Panel Methods Playlist
https://www.youtube.com/watch?v=bWjo3N9COz4&list=PLxT-itJ3HGuUDVMuWKBxyoY8Dm9O9qstP
NOTES
- Ill add notes here if I need to.
ERRORS
- If you see an error in the video, please let me know and I will include it here.
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
https://amzn.to/3emVuXU
► Foundations of Aerodynamics, Kuethe and Chow
https://amzn.to/2yMg1Vi
► Theory of Wing Sections, Abbott and Doenhoff
https://amzn.to/2wvZyUt Streamline Geometric Integral VPM [Nx(pj) and Ny(pj)]](https://i.ytimg.com/vi/TBwBnW87hso/mqdefault.jpg)





![Explained: Popup Menu GUI [MATLAB]
Pop-up menus can be used to make a selection from a list of items. This video shows how to get the users input from a pop-up menu in a MATLAB GUI.
Tip:
The method described in the video gives you a little bit more information to work with when extracting data from the popup menu, but if you want the most efficient code, you can use the code below.
popVal = get(hObject,Value);
assignin(base,popVal,popVal);
In this code, youre simply getting the selected value. The first choice is 1, the second choice is 2, and so on. You can then immediately assign this variable back into the base workspace. This code is much simpler, but you also wont have a variable with the strings of all the choices available. In most of my applications, I dont care about the actual strings, just about the value thats selected. Explained: Popup Menu GUI [MATLAB]](https://i.ytimg.com/vi/Wv6aSJ6ifaQ/mqdefault.jpg)
![Explained: Check Box GUI [MATLAB]
A check box can be used for selection or deselection of an option. This video describes how to get the status of a check box in a MATLAB GUI.
Download the code from my website:
http://goo.gl/jSWqAH Explained: Check Box GUI [MATLAB]](https://i.ytimg.com/vi/XUdhhLyJHBg/mqdefault.jpg)

![Afterburners: Why the Nozzle Opens Wider with Afterburner On
In this video Ill go through an example showing why the nozzle on a jet engine needs to open up wider when the afterburner is on. You can tell that an afterburner is on when you see the visible radiation in the afterburner/jet pipe.
Ill be making some more in-depth videos about converging nozzles, converging-diverging nozzles, nozzle flow, choked flow, etc. If you havent already, subscribe so you can be notified when I post them!
NOTES
► Quick note regarding flow choking: You can increase the mass flow rate even when the flow is choked by increasing the upstream stagnation pressure. When I said you couldnt increase the mass flow rate anymore, it was for a fixed stagnation pressure, because thats what you usually have coming out of the turbine of the engine. So that plot on the board is valid for a fixed P_0, when we keep decreasing P.
REFERENCE VIDEOS
→ Turbojet Thrust Equation:
https://goo.gl/gyaalq
→ Stagnation Relations:
https://goo.gl/yOSNeL
→ Isentropic Relations:
https://goo.gl/vxhrLH
→ Speed of Sound:
https://goo.gl/3qZhII
ASSUMPTIONS AND NOTES
1) The nozzle is isentropic.
- Adiabatic: no heat is added or removed.
- Reversible: no friction, shocks, etc.
2) The working fluid is air. Of course the actual working fluid will be the mixture of air and combustion products. This assumption avoids extra calculations that can certainly be done, but are unnecessary for the outcome of this example.
3) The air is a calorically perfect gas (specific heats are constant).
4) The engine is fitted with a converging nozzle (not converging-diverging).
5) The direct result of turning the afterburner on results in an increase in the stagnation temperature of the fluid.
6) The flow is steady through the nozzle.
7) The flow is quasi-1D.
8) Mass flow rate and stagnation pressure do not change when the afterburner is turned on.
9) Values used are just characteristic numbers that might be valid for real engines.
10) If you do have a converging-diverging nozzle, then to get supersonic flow (higher exit velocities), you will still need to have choked flow. In order to increase subsonic flow to supersonic flow in a CD nozzle, the nozzle must be choked.
THUMBNAIL IMAGE
Photo: SAC Ben Stevenson/MOD [OGL http://www.nationalarchives.gov.uk/doc/open-government-licence/version/1/)], via Wikimedia Commons Afterburners: Why the Nozzle Opens Wider with Afterburner On](https://i.ytimg.com/vi/YKCqyaYMSs8/mqdefault.jpg)
