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Panel method for NACA XXXX aerofoils

version (5.16 KB) by Alexander Giles
Panel method using doublets and sources with the Dirichlet boundary condition


Updated 31 Aug 2015

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Following the implementation of Katz and Plotkin, this code simulates the performance of an aerofoil in steady flow assuming that the flow remains attached and viscous effects can be ignored.

Cite As

Alexander Giles (2021). Panel method for NACA XXXX aerofoils (, MATLAB Central File Exchange. Retrieved .

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

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