NACA 4 digit Airfoil Generator

Generates the NACA 4 digit airfoil coordinates

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 submission has inspired the following:; XFOIL - MATLAB interface
• MATLAB release: MATLAB 7.4 (R2007a)

[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.

[ZeRO LiFT]

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

[Amet Ervin]

 

[yaad ram]