Uploaded May 2015 | Updated September 2026, 1 week ago
This is the fourth 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 code the airfoil type callback. This edit text box reads in the string of the airfoil that the user wants to compute and plot. After we read in the value of the airfoil, we check to make sure that it is only four digits. If more or less, it displays an error message and makes sure the airfoil can't be plotted.
IN THIS SERIES:
Part 1/10 : goo.gl/9UBgbo
Part 2/10 : goo.gl/jRRcYJ
Part 3/10 : goo.gl/rSVLHo
Part 4/10 : goo.gl/HwHB39
Part 5/10 : goo.gl/AlDne8
Part 6/10 : goo.gl/7n1QP7
Part 7/10 : goo.gl/nTGleR
Part 8/10 : goo.gl/ez247P
Part 9/10 : goo.gl/8mXYcc
Part 10/10: goo.gl/ovBlbW
This is the fourth 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 code the airfoil type callback. This edit text box reads in the string of the airfoil that the user wants to compute and plot. After we read in the value of the airfoil, we check to make sure that it is only four digits. If more or less, it displays an error message and makes sure the airfoil can't be plotted.
IN THIS SERIES:
Part 1/10 : goo.gl/9UBgbo
Part 2/10 : goo.gl/jRRcYJ
Part 3/10 : goo.gl/rSVLHo
Part 4/10 : goo.gl/HwHB39
Part 5/10 : goo.gl/AlDne8
Part 6/10 : goo.gl/7n1QP7
Part 7/10 : goo.gl/nTGleR
Part 8/10 : goo.gl/ez247P
Part 9/10 : goo.gl/8mXYcc
Part 10/10: goo.gl/ovBlbW

![Explained: Radio Button GUI [MATLAB]
A radio button can be used for selection and deselection of an option. This video shows how to get the value of a radio button in a MATLAB GUI. Explained: Radio Button GUI [MATLAB]](https://i.ytimg.com/vi/xN2fMYZgEOw/mqdefault.jpg)

![Explained: NACA 4-Digit GUI Part 7/10 [MATLAB]
This is the seventh 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 code the four popup menus that appear in the GUI: Grid Type, Trailing Edge, Plot As, and Save Style.
Popup Menu Video:
https://goo.gl/aY6DoQ
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 Explained: NACA 4-Digit GUI Part 7/10 [MATLAB]](https://i.ytimg.com/vi/x_iOVeqJCLA/mqdefault.jpg)

![Explained: Flap Track Fairings/Whitcomb Area Rule [Airplanes]
What are flap track fairings and what purpose do they serve on an airplane? These canoe-shaped pieces house linkages and mechanisms that connect the flaps to the wing. As an added bonus (if designed correctly), they can help decrease the wave drag by something known as area-ruling.
Reference(s):
http://www.aerospaceweb.org/question/aerodynamics/q0240.shtml Explained: Flap Track Fairings/Whitcomb Area Rule [Airplanes]](https://i.ytimg.com/vi/y100a_nB984/mqdefault.jpg)

![Explained: Selectively Delete Plots in GUI [MATLAB]
This video describes how to plot two lines on the same plot in a GUI axes object, and then selectively delete each of the lines using push buttons. Explained: Selectively Delete Plots in GUI [MATLAB]](https://i.ytimg.com/vi/ysaj4K7PRHI/mqdefault.jpg)
![Explained: Constant Total Enthalpy [Taylor-Maccoll]
In order to use Croccos Theorem for the Taylor-Maccoll problem, it is necessary to show why the total enthalpy along a streamline is constant (within the given assumptions). We start with the energy equation couched in terms of the total enthalpy, and reduce the equation with our assumptions from a previous video in this series. The final result will be used in the derivation of Croccos Theorem. Explained: Constant Total Enthalpy [Taylor-Maccoll]](https://i.ytimg.com/vi/yy5HQ9syrrI/mqdefault.jpg)
![Source Panel Method: Circular Cylinder
Here we are. We finally have all the mathematical information needed to code up the source panel method. In this video, we take the code we had from the panel method geometry video, and add in the following: computation of the source panel strengths, computation of the panel tangential velocities and pressure coefficients, and computation of the grid X and Y velocities (for streamline plotting).
This video uses a circular cylinder geometry because it is a convenient test case where we can compare the pressure coefficients on the panels to an analytical solution. If your code doesnt work with a circular cylinder, its not a good idea to move on to harder geometries.
WHERE ARE WE GOING?
→ The next video will be very similar to this one; the source panel method solution for airfoil geometries.
→ We will see some limitations in the SPM which will motivate the need for the vortex panel method (VPM).
→ I will need to go through the derivations for the geometric integrals for the VPM (which are similar to the SPM derivations).
→ We will then implement the VPM and see some of its limitations. These limitations will motivate the need for a more robust implementation of the VPM.
→ I will derive the combined SPM/VPM formulation and code it to show how good we can get the results for a pretty simple implementation.
→ We can finally extend the SPM/VPM formulation to multiple separate airfoil elements. This will be the last video in the series.
CODE
► My website
http://www.joshtheengineer.com/2020/02/29/source-panel-method-circular-cylinder/
► GitHub
https://github.com/jte0419/Panel_Methods
RELEVANT VIDEOS
► Panel Methods Playlist
https://www.youtube.com/watch?v=bWjo3N9COz4&list=PLxT-itJ3HGuUDVMuWKBxyoY8Dm9O9qstP
► Panel Method Geometry
https://www.youtube.com/watch?v=kIqxbd937PI
► Building More Complex Flows
https://www.youtube.com/watch?v=EKzbwJvKcmw
► Flow Around an Airfoil
https://www.youtube.com/watch?v=cLdv1UfX1g8
► Normal Velocity Geometric Integral [I(ij)]
https://www.youtube.com/watch?v=76vPudNET6U
► Tangential Velocity Geometric Integral [J(ij)]
https://www.youtube.com/watch?v=JRHnOsueic8
► Streamline Geometric Integral SPM [Mx(ij) and My(ij)]
https://www.youtube.com/watch?v=BnPZjGCatcg
► Solving the System of Equations
https://www.youtube.com/watch?v=ep7vPzGYsbw
NOTES
→ I forgot to add the pop filter in front of my microphone for this video, so I apologize in advance.
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 Source Panel Method: Circular Cylinder](https://i.ytimg.com/vi/zIrDfEz-5mc/mqdefault.jpg)
