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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 (2026). NACA.m (https://in.mathworks.com/matlabcentral/fileexchange/47838-naca-m), MATLAB Central File Exchange. Retrieved .
Acknowledgements
Inspired: drawing a NACA 65 series airofoil
General Information
- Version 1.0.0.0 (1.85 KB)
MATLAB Release Compatibility
- Compatible with any release
Platform Compatibility
- Windows
- macOS
- Linux
| Version | Published | Release Notes | Action |
|---|---|---|---|
| 1.0.0.0 |
