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

版本 2.0.0.0 (8.7 KB) 作者: Alexander Giles
Constant strength doublet panel method for evaluating pressure distribution for symmetric NACA foils
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更新时间 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.

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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. 检索来源 .

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版本 已发布 发行说明
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.