Uploaded November 2017 | Updated September 2026, 2 weeks ago
Let's calculate the mass flow rate through the Rocketdyne F-1 engine used to power the Saturn V! We will use the equation for the mass flow rate that I derived in a previous video (see below). At the end, we can compare the value we calculated to the actual value given in the engine specs.
===== NOTES =====
► There are different values of the variables that I am using in this problem, which will change the mass flow rate slightly. The key is that these values give a pretty good approximation of the mass flow rate.
===== RELEVANT LINKS =====
→ CEA Online
cearun.grc.nasa.gov
→ F-1 Engine Specs
en.wikipedia.org/wiki/Rocketdyne_F-1
===== RELEVANT VIDEOS =====
→ Nozzle Mass Flow Rate
goo.gl/d6AoFX
→ Converging-Diverging Nozzle
goo.gl/jrsyoJ
→ Sonic State (Critical, Star)
goo.gl/vhjESy
→ Area-Mach Number Relation [CPG]
goo.gl/j4FwQX
===== THUMBNAIL IMAGE =====
By NASA Marshall Space Flight Center (nix.nasa.gov/info?id=MSFC-6862846) [Public domain], via Wikimedia Commons
Let's calculate the mass flow rate through the Rocketdyne F-1 engine used to power the Saturn V! We will use the equation for the mass flow rate that I derived in a previous video (see below). At the end, we can compare the value we calculated to the actual value given in the engine specs.
===== NOTES =====
► There are different values of the variables that I am using in this problem, which will change the mass flow rate slightly. The key is that these values give a pretty good approximation of the mass flow rate.
===== RELEVANT LINKS =====
→ CEA Online
cearun.grc.nasa.gov
→ F-1 Engine Specs
en.wikipedia.org/wiki/Rocketdyne_F-1
===== RELEVANT VIDEOS =====
→ Nozzle Mass Flow Rate
goo.gl/d6AoFX
→ Converging-Diverging Nozzle
goo.gl/jrsyoJ
→ Sonic State (Critical, Star)
goo.gl/vhjESy
→ Area-Mach Number Relation [CPG]
goo.gl/j4FwQX
===== THUMBNAIL IMAGE =====
By NASA Marshall Space Flight Center (nix.nasa.gov/info?id=MSFC-6862846) [Public domain], via Wikimedia Commons
![Explained: Waitbar Color Change [MATLAB]](https://i.ytimg.com/vi/IjkajdAE8vA/mqdefault.jpg "Explained: Waitbar Color Change [MATLAB]
This video shows how you can change the color of your waitbar (progress bar) in your MATLAB code.
Basic waitbar video: http://www.youtube.com/watch?v=k2wKPxRUPiE")
![Vortex Panel Method: Tangential Velocity Geometric Integral [L(ij)]](https://i.ytimg.com/vi/IxWJzwIG_gY/mqdefault.jpg "Vortex Panel Method: Tangential Velocity Geometric Integral [L(ij)]
We just finished the video for the source panel method (SPM), and saw its inherent limitations as we looked at some results for an airfoil. Now, to be able to code up the vortex panel method (VPM), we need to compute geometric integrals similar to those for the SPM. These geometric integrals come from the expressions for the normal and tangential velocity.
In this video, we derive the geometric integral from the tangential velocity expression (Lij). In the next video, we will derive the X and Y velocity expression geometric integrals needed for the streamline calculations, after which we can construct a system of equations to solve for the vortex panel strengths.
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")
![Explained: NACA 4-Digit GUI Part 5/10 [MATLAB]](https://i.ytimg.com/vi/J0L7N7cvk80/mqdefault.jpg "Explained: NACA 4-Digit GUI Part 5/10 [MATLAB]
This is the fifth 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 input for the angle of attack and save file name edit text boxes. The angle of attack text box needs to be converted to a number, while the file name text box can remain a string.
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: Ghost Nodes [CFD]](https://i.ytimg.com/vi/JMP9aanQ5o0/mqdefault.jpg "Explained: Ghost Nodes [CFD]
In some finite difference/volume equations, you might need to use points that are outside of the actual grid domain. In these cases, ghost nodes can be calculated from the interior points and used for the differences (such as a central difference on a boundary node).")
![Source Panel Method: Tangential Velocity Geometric Integral [J(ij)]](https://i.ytimg.com/vi/JRHnOsueic8/mqdefault.jpg "Source Panel Method: Tangential Velocity Geometric Integral [J(ij)]
In the previous video (Geometric Integral Iij), we went through the full derivation of the geometric integral for the normal partial derivative, which was needed to solve for the source panel strengths. In this video, we will go through the (very similar) derivation of the tangential partial derivative geometric integral, which is needed to solve for the panel velocities, and thus the panel pressure coefficients.
This derivation is almost exactly the same as the normal geometric integral derivation, but there are some slight differences. Where it is exactly the same, I will refer you back to my other video (Iij) so we dont make this video longer than it needs to be.
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, Iij
https://www.youtube.com/watch?v=76vPudNET6U
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")
