Simple panel method model for evaluating pressure distribution over symmetric NACA aerofoils
Constant strength doublet panel method for evaluating pressure distribution for symmetric NACA foils
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Following the formulation described in Katz and Plotkin's 'Low-Speed Aerodynamics', this is a simple panel method for predicting pressure distributions over symmetric NACA aerofoils applying the Neumann boundary condition (zero flow normal to a body surface). This has been kept simple to help beginners (like myself) get to grips with the panel code approach.
Cite As
Alexander Giles (2026). Simple panel method model for evaluating pressure distribution over symmetric NACA aerofoils (https://uk.mathworks.com/matlabcentral/fileexchange/52264-simple-panel-method-model-for-evaluating-pressure-distribution-over-symmetric-naca-aerofoils), MATLAB Central File Exchange. Retrieved .
General Information
- Version 2.0.0.0 (8.69 KB)
MATLAB Release Compatibility
- Compatible with any release
Platform Compatibility
- Windows
- macOS
- Linux
