NACA method for calculus of pressure coefficent distribution

version 1.1.0 (2.32 KB) by Amedeo Falco
With this script you can calculate a pressure coefficent distribution around any profile of the four digit NACA series

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Updated Tue, 24 May 2022 15:13:48 +0000

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With this script you can calculate a pressure coefficent distribution around any profile of the four digit NACA series.
1) V_v is the ratio velocity for symmetric airfoil at 0° AOA
2) Delta_va_V is the distribution of velocity for symmetric airfoli
3) Delta_v_V is the distribution of velocity for mean line at Cl_i and AOA_i (where i = ideal)
4) f_alpha is a correction factor caculate as difference between desiderate C_l and Cl_i , considering a Cl_0 = 1 relative at the AOA_i

Cite As

Amedeo Falco (2022). NACA method for calculus of pressure coefficent distribution (https://www.mathworks.com/matlabcentral/fileexchange/112135-naca-method-for-calculus-of-pressure-coefficent-distribution), MATLAB Central File Exchange. Retrieved .

MATLAB Release Compatibility
Created with R2022a
Compatible with any release
Platform Compatibility
Windows macOS Linux

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