NACA.m

Version 1.0.0.0 (1.85 KB) by manos
Naca0012
0.0
(0)
327 Downloads
Updated 15 Sep 2014

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It calculates lift,drag and moment coeficients for an airfoil. You must provide data file (A.dat) with x,y coordinates and pressure+shear stress values

Cite As

manos (2024). NACA.m (https://www.mathworks.com/matlabcentral/fileexchange/47838-naca-m), MATLAB Central File Exchange. Retrieved .

MATLAB Release Compatibility
Created with R2010b
Compatible with any release
Platform Compatibility
Windows macOS Linux
Categories
Find more on Airfoil tools in Help Center and MATLAB Answers
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Acknowledgements

Inspired: drawing a NACA 65 series airofoil

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Version Published Release Notes
1.0.0.0