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

version 2.0.0.0 (8.69 KB) by Alexander Giles
Constant strength doublet panel method for evaluating pressure distribution for symmetric NACA foils

24 Downloads

Updated 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.

Cite As

Alexander Giles (2021). 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. Retrieved .

Comments and Ratings (3)

SUN Young

thanks for your work.
but I can not understand line 71, why sin theta=-sin(theta)?

Alexander Giles

Note - the aerofoil setting when this file was uploaded was a very thick aerofoil. NACA 00XX aerofoils are normally XX < 20

MATLAB Release Compatibility
Created with R2014b
Compatible with any release
Platform Compatibility
Windows macOS Linux

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