jahuwaldt.aero.airfoils

Class NACA65ASeries

java.lang.Object

jahuwaldt.aero.airfoils.NACA6Series

jahuwaldt.aero.airfoils.NACA6ASeries

jahuwaldt.aero.airfoils.NACA65ASeries

All Implemented Interfaces:

Airfoil, java.io.Serializable

public class NACA65ASeries
extends NACA6ASeries

This class represents an arbitrary NACA 65A series airfoil section such as a NACA 65A020 airfoil.

Ported from FORTRAN "NACA6.FOR" to Java by: Joseph A. Huwaldt, June 4, 2010

Original FORTRAN "NACA4" code had the following note:

         AUTHORS - Charles L.Ladson and Cuyler W. Brooks, NASA Langley
                   Liam Hardy, NASA Ames
                   Ralph Carmichael, Public Domain Aeronautical Software
         Last FORTRAN version:  23Nov96  2.0   RLC

         NOTES - This program has also been known as LADSON and SIXSERIES and
                 as SIXSERIE on systems with a 8-letter name limit.
         REFERENCES-  NASA Technical Memorandum TM X-3069 (September, 1974),
                      by Charles L. Ladson and Cuyler W. Brooks, Jr., NASA Langley Research Center.

                      "Theory of Wing Sections", by Ira Abbott and Albert Von Doenhoff.
  

Modified by: Joseph A. Huwaldt

Version:

September 15, 2012

Author:

Joseph A. Huwaldt Date: June 6, 2010

See Also:

Serialized Form

Constructor Summary

Constructors

Constructor and Description
NACA65ASeries(double CLi, double thickness, double length) Create a NACA 65A series airfoil with the specified parameters.

Method Summary

Modifier and Type	Method and Description
java.lang.String	getProfile() Returns a String that represents the profile type of this airfoil.
static void	main(java.lang.String[] args) Simple method to test this class.

Methods inherited from class jahuwaldt.aero.airfoils.NACA6Series

getCamber, getLower, getLowerYp, getUpper, getUpperYp, toString

Methods inherited from class java.lang.Object

equals, getClass, hashCode, notify, notifyAll, wait, wait, wait

Constructor Detail

NACA65ASeries

public NACA65ASeries(double CLi,
                     double thickness,
                     double length)

Create a NACA 65A series airfoil with the specified parameters.

Parameters:

CLi - Design lift coefficient (e.g.: 65A206 has CLi = 0.2).

thickness - The thickness to chord ratio (e.g.: 0.20 ==> 20% t/c).

length - The chord length.

Method Detail

getProfile

public java.lang.String getProfile()

Returns a String that represents the profile type of this airfoil.

Specified by:

getProfile in class NACA6Series

main

public static void main(java.lang.String[] args)

Simple method to test this class.