Panel method for NACA XXXX aerofoils
Panel method using doublets and sources with the Dirichlet boundary condition
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Following the implementation of Katz and Plotkin, this code simulates the performance of an aerofoil in steady flow assuming that the flow remains attached and viscous effects can be ignored.
Cite As
Alexander Giles (2026). Panel method for NACA XXXX aerofoils (https://www.mathworks.com/matlabcentral/fileexchange/52771-panel-method-for-naca-xxxx-aerofoils), MATLAB Central File Exchange. Retrieved .
General Information
- Version 1.0.0.0 (5.16 KB)
MATLAB Release Compatibility
- Compatible with any release
Platform Compatibility
- Windows
- macOS
- Linux
| Version | Published | Release Notes | Action |
|---|---|---|---|
| 1.0.0.0 |
