Simple panel method model for evaluating pressure distribution over symmetric NACA aerofoils

Version 2.0.0.0 (8,69 KB) von Alexander Giles
Constant strength doublet panel method for evaluating pressure distribution for symmetric NACA foils
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Aktualisiert 31. Aug 2015

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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.

Zitieren als

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. Abgerufen .

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Erstellt mit R2014b
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Version Veröffentlicht Versionshinweise
2.0.0.0

Thickness by chord instead of thickness (correction in the definition of the aerofoil).
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.