Uploaded November 2016 | Updated September 2026, 2 weeks ago
In this video we will derive the stagnation-to-static relations for pressure, density, and temperature. Specifically, these derivations will be carried out in a form that is valid for compressible flow.
===== RELEVANT VIDEOS =====
→ Turbofan Inlet
goo.gl/0s7nSR
→ 1D Energy Eqn
goo.gl/RSXVyc
→ Thermally Perfect Gas
goo.gl/maElnm
→ Specific Heats
goo.gl/kdf1B7
→ Isentropic Relations
goo.gl/Q8Rv9O
===== REFERENCES =====
► Notes by Matt MacLean
► Modern Compressible Flow, Anderson
► Elements of Gasdynamics, Liepmann and Roshko
► Gas Dynamics, Zucrow and Hoffman
In this video we will derive the stagnation-to-static relations for pressure, density, and temperature. Specifically, these derivations will be carried out in a form that is valid for compressible flow.
===== RELEVANT VIDEOS =====
→ Turbofan Inlet
goo.gl/0s7nSR
→ 1D Energy Eqn
goo.gl/RSXVyc
→ Thermally Perfect Gas
goo.gl/maElnm
→ Specific Heats
goo.gl/kdf1B7
→ Isentropic Relations
goo.gl/Q8Rv9O
===== REFERENCES =====
► Notes by Matt MacLean
► Modern Compressible Flow, Anderson
► Elements of Gasdynamics, Liepmann and Roshko
► Gas Dynamics, Zucrow and Hoffman
![Explained: Linspace [MATLAB]](https://i.ytimg.com/vi/PA4hJy48eJw/mqdefault.jpg "Explained: Linspace [MATLAB]
In this video I show you how to use the linspace function in MATLAB to easily create arrays.")
![Explained: NACA 4-Digit Airfoil MATLAB Code [Airplanes]](https://i.ytimg.com/vi/QezOan1pVgs/mqdefault.jpg "Explained: NACA 4-Digit Airfoil MATLAB Code [Airplanes]
This video goes through a step-by-step description of the coding of a program to calculate the coordinates of a NACA 4-digit airfoil.
If you would like to know where the equations come from, please see my previous video, located here:
http://goo.gl/FcufZh
To download a GUI I made from this code, visit my GitHub linked to here:
https://github.com/jte0419/NACA_4_Digit_Airfoil")
