JoshTheEngineer | How To: Run XFoil from MATLAB @JoshTheEngineer | Uploaded January 2019 | Updated October 2024, 2 hours ago.
This video shows how to run XFoil from a MATLAB script (for a Python script, see link below). This will come in handy for my future Vortex Panel Method video, where we will compare our pressure coefficient and lift coefficient results with the XFoil results. We'll go through three steps in this video.
1) Run XFoil and output the files we need (airfoil coordinates and pressure coefficient)
2) Load saved files from XFoil into MATLAB and view plots
3) Run XFoil from the MATLAB script itself, and view plots
===== RELEVANT LINKS =====
► You can download the MATLAB script from my website
joshtheengineer.com/2019/01/30/running-xfoil-from-matlab
► Do you want to run XFoil from Python instead? Download the script from my website
joshtheengineer.com/2019/02/06/running-xfoil-from-python
► Download XFoil
https://web.mit.edu/drela/Public/web/xfoil/
GitHub: Panel Methods
► github.com/jte0419/Panel_Methods
===== RELEVANT VIDEOS =====
UIUC Airfoil Database Download Python Code
→ youtube.com/watch?v=nILo18DlqAo
Load Airfoil Coordinates from UIUC Files into MATLAB
→ youtube.com/watch?v=xJYxMfGFrk8
Panel Method Motivation and Introduction
→ Coming soon!
Panel Method Geometry Definitions
→ Coming soon!
Source Panel Derivation and Coding
→ Coming soon!
Vortex Panel Derivation and Coding
→ Coming soon!
===== NOTES =====
► This is not a comprehensive XFoil user guide video. I'm only running the commands I need for my future Vortex Panel Method video.
► If you just want the NACA 4-digit airfoil coordinates, you can also use my NACA 4-Digit Airfoil MATLAB code to generate them.
This video shows how to run XFoil from a MATLAB script (for a Python script, see link below). This will come in handy for my future Vortex Panel Method video, where we will compare our pressure coefficient and lift coefficient results with the XFoil results. We'll go through three steps in this video.
1) Run XFoil and output the files we need (airfoil coordinates and pressure coefficient)
2) Load saved files from XFoil into MATLAB and view plots
3) Run XFoil from the MATLAB script itself, and view plots
===== RELEVANT LINKS =====
► You can download the MATLAB script from my website
joshtheengineer.com/2019/01/30/running-xfoil-from-matlab
► Do you want to run XFoil from Python instead? Download the script from my website
joshtheengineer.com/2019/02/06/running-xfoil-from-python
► Download XFoil
https://web.mit.edu/drela/Public/web/xfoil/
GitHub: Panel Methods
► github.com/jte0419/Panel_Methods
===== RELEVANT VIDEOS =====
UIUC Airfoil Database Download Python Code
→ youtube.com/watch?v=nILo18DlqAo
Load Airfoil Coordinates from UIUC Files into MATLAB
→ youtube.com/watch?v=xJYxMfGFrk8
Panel Method Motivation and Introduction
→ Coming soon!
Panel Method Geometry Definitions
→ Coming soon!
Source Panel Derivation and Coding
→ Coming soon!
Vortex Panel Derivation and Coding
→ Coming soon!
===== NOTES =====
► This is not a comprehensive XFoil user guide video. I'm only running the commands I need for my future Vortex Panel Method video.
► If you just want the NACA 4-digit airfoil coordinates, you can also use my NACA 4-Digit Airfoil MATLAB code to generate them.
![Explained: Area-Mach Number Relation [CPG]](https://i.ytimg.com/vi/bdcxN0u5hMs/hqdefault.jpg "Explained: Area-Mach Number Relation [CPG]
Can we approximate the exit Mach number of a rocket nozzle knowing only the area ratio? With a few assumptions, we certainly can! In fact, if we know how the area changes along a nozzle from the throat to the exit, we can calculate how the Mach number varies throughout the entire nozzle.
NOTES
► Ill make sure to never use my orange marker again
► If you download my Method of Characteristics MATLAB code from my GitHub (link below), you can see that the results of both match very closely!
HOW TO SOLVE AREA-MACH NUMBER RELATION
http://www.joshtheengineer.com/2016/11/16/solving-the-area-mach-number-relation/
ROCKET NOZZLE - METHOD OF CHARACTERISTICS
https://github.com/jte0419/Rocket_Nozzle_Design
RELEVANT VIDEOS
Area-Mach Number Differential Form
https://goo.gl/tDzBtM
Sonic State
https://goo.gl/j6yCxD
Stagnation-to-Static Relations
https://goo.gl/r5JZSQ
Normal Shock Relations
https://goo.gl/E5Lwac
REFERENCES
► Notes by Matt MacLean
► Modern Compressible Flow, Anderson
► Elements of Gasdynamics, Liepmann and Roshko
► Gas Dynamics, Zucrow and Hoffman
THUMBNAIL IMAGE
By NASA (http://mix.msfc.nasa.gov/abstracts.php?p=2388) [Public domain], via Wikimedia Commons")
![Explained: Pitch Stiffness [Flight Dynamics]](https://i.ytimg.com/vi/bo68hptU6YA/hqdefault.jpg "Explained: Pitch Stiffness [Flight Dynamics]
Explained: Pitch Stiffness [Flight Dynamics]")
![Explained: Static Text GUI [MATLAB]](https://i.ytimg.com/vi/cWZLGpaVwwE/hqdefault.jpg "Explained: Static Text GUI [MATLAB]
Static text fields can be used to indicate the status of your program, or simply to write text or numbers. This video describes how to set the static text field in a MATLAB GUI.")
![Explained: Critical Mach Number [Airplanes]](https://i.ytimg.com/vi/e3BWJZIvXQ4/hqdefault.jpg "Explained: Critical Mach Number [Airplanes]
Explained: Critical Mach Number [Airplanes]")
![Explained: NACA 4-Digit GUI Part 8/10 [MATLAB]](https://i.ytimg.com/vi/eW8eEJtwRqA/hqdefault.jpg "Explained: NACA 4-Digit GUI Part 8/10 [MATLAB]
This is the eighth 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 radio button for showing the camber line of the airfoil. We also code the Exit button.
Radio Button Video:
https://goo.gl/E4Owva
Exit Button Video:
https://goo.gl/aarwmW
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")
