Uploaded November 2016 | Updated September 2026, 2 weeks ago
In this video, we will go through the derivation of why, for a thermally perfect gas (TPG), the energy and enthalpy are only a function of temperature, and not of two state variables. We will be using the combined 1st & 2nd law of thermodynamics (video [1] below for derivation).
===== RELEVANT VIDEOS =====
[1] : goo.gl/soiSr9
===== 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 go through the derivation of why, for a thermally perfect gas (TPG), the energy and enthalpy are only a function of temperature, and not of two state variables. We will be using the combined 1st & 2nd law of thermodynamics (video [1] below for derivation).
===== RELEVANT VIDEOS =====
[1] : goo.gl/soiSr9
===== REFERENCES =====
:: Notes by Matt MacLean
:: Modern Compressible Flow, Anderson
:: Elements of Gasdynamics, Liepmann and Roshko
:: Gas Dynamics, Zucrow and Hoffman
![Explained: NACA 4-Digit GUI Part 2/10 [MATLAB]](https://i.ytimg.com/vi/spHG_XEP5-c/mqdefault.jpg "Explained: NACA 4-Digit GUI Part 2/10 [MATLAB]
This is the second 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 clean up the GUI layout after opening the .fig file in GUIDE. We make the widths of the components the same, as well as align boxes and buttons horizontally and vertically.
IN THIS SERIES:
Part 1/10 : https://goo.gl/9UBgbo
Part 2/10 : https://goo.gl/jRRcYJ
Part 3/10 : https://www.youtube.com/watch?v=SbW1NDuvdJQ
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: Lift Curve [Airplanes]](https://i.ytimg.com/vi/tF_Z1lz7HKw/mqdefault.jpg "Explained: Lift Curve [Airplanes]
Lift curves are available for various airfoils and provide data relating the lift coefficient of the airfoil to the angle of attack. The lift curves described in this video are for 2D (infinite wing) airfoils. Actual 3D wing lift curves are complicated by 3D effects such as spanwise flow and tip vortices. See the links below for actual NACA data for both a symmetric and a cambered airfoil.
Angle of Attack:
https://www.youtube.com/watch?v=Fm2Az-PgPUU
NACA 0012 (Symmetric):
- The lift curve to look at is the lower of the two sloped lines
- Notice that at zero AoA, the lift coefficient is zero
- The horizontal lines are moment coefficient plots, which you can ignore for now
http://mshades.free.fr/flapping/Cz0012.jpg
NACA 2412 (Cambered):
- Lift curve is the left of the two plots
- Notice that the zero lift AoA is negative (approx. -2 degrees)
http://www.tricity.wsu.edu/htmls/mme/me439/s2007/naca2412.jpg")
