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NACA 4 digit Airfoil Generator

4.4

4.4 | 5 ratings Rate this file 197 Downloads (last 30 days) File Size: 2.81 KB File ID: #19915
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NACA 4 digit Airfoil Generator

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14 May 2008 (Updated )

Generates the NACA 4 digit airfoil coordinates

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File Information
Description

"naca4gen.m" Generates the NACA 4 digit airfoil coordinates with desired no. of panels (line elements) on it.

FEATURES:
 *Accurate coordinate generation with the required precision
 *Option to generate closed or open Trailing Edge
 *Additional separate outputs for camber line, upper surface and lower surface
 *A tst (test) file included

INPUTS:
[1] NACA 4 digit designation (eg. '2412')
[2] No of panels (line elements) PER SIDE (upper/lower)
[3] Type of chord station spacing (Half cosine spacing / Uniform spacing)

OUTPUTS:
[1] One can plot the generated airfoil, camber line and the leading edge circle by setting an option input wantPlot=1
[2] A data file can be generated by setting the option input wantFile=1

EXTENSION:
Being a function, the airfoil generator can be called several times from a loop to generate any number of airfoil data files.

Acknowledgements

This file inspired Xfoil Matlab Interface.

MATLAB release MATLAB 7.4 (R2007a)
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Comments and Ratings (6)
24 Sep 2014 Tanon Chompoopol  
23 Mar 2012 David Taylor  
13 Jan 2011 yaad ram  
24 Sep 2009 Amet Ervin  
22 Feb 2009 ZeRO LiFT

good , check step , check a2 , then check the camber ,good luck

16 Sep 2008 yelko huacoto

Hola amigo, en realidad me parece muy noble de tu parte colgar la programacion del naca asi me puedo guiar para proximos trabajos.

Updates
12 Feb 2009

 *Option to generate closed or open Trailing Edge
 *Additional separate outputs for camber line, upper surface and lower surface
 *A tst (test) file included

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