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

バージョン 2.0.0.0 (8.69 KB) 作成者: Alexander Giles
Constant strength doublet panel method for evaluating pressure distribution for symmetric NACA foils
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更新 2015/8/31

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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.

引用

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. 取得済み .

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バージョン 公開済み リリース ノート
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.