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 (2026). 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
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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 |
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