Panel method for NACA XXXX aerofoils

Versione 1.0.0.0 (5,16 KB) da Alexander Giles
Panel method using doublets and sources with the Dirichlet boundary condition
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Aggiornato 31 ago 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.

Cita come

Alexander Giles (2024). Panel method for NACA XXXX aerofoils (https://www.mathworks.com/matlabcentral/fileexchange/52771-panel-method-for-naca-xxxx-aerofoils), MATLAB Central File Exchange. Recuperato .

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Versione Pubblicato Note della release
1.0.0.0