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

Versión 2.0.0.0 (8,69 KB) por Alexander Giles
Constant strength doublet panel method for evaluating pressure distribution for symmetric NACA foils
5.0
(2)
1,1K descargas
Actualizado 31 ago 2015

Ver licencia

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.

Citar como

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. Recuperado .

Compatibilidad con la versión de MATLAB
Se creó con R2014b
Compatible con cualquier versión
Compatibilidad con las plataformas
Windows macOS Linux
Categorías
Más información sobre Thermal Analysis en Help Center y MATLAB Answers.

Community Treasure Hunt

Find the treasures in MATLAB Central and discover how the community can help you!

Start Hunting!

Versión Publicado Notas de la versión
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.