Simple panel method model for evaluating pressure distribution over symmetric NACA aerofoils
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.
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Alexander Giles (2024). Simple panel method model for evaluating pressure distribution over symmetric NACA aerofoils (https://www.mathworks.com/matlabcentral/fileexchange/52264-simple-panel-method-model-for-evaluating-pressure-distribution-over-symmetric-naca-aerofoils), MATLAB Central File Exchange. Récupéré le .
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- Sciences > Material Sciences > Thermal Analysis >
- Engineering > Aerospace Engineering > Aerodynamics >
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Version | Publié le | Notes de version | |
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2.0.0.0 | Thickness by chord instead of thickness (correction in the definition of the aerofoil). |
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1.0.0.0 | Correction of line 268. Consequence is a significant improvement in the pressure coefficient on the top side at the leading edge. |