Package jahuwaldt.aero.airfoils

Class NACA4ModCambered

java.lang.Object

jahuwaldt.aero.airfoils.NACA4Uncambered

jahuwaldt.aero.airfoils.NACA4ModUncambered

jahuwaldt.aero.airfoils.NACA4ModCambered

All Implemented Interfaces:

Airfoil, java.io.Serializable

public class NACA4ModCambered
extends NACA4ModUncambered

This class represents an arbitrary cambered NACA modified 4 digit airfoil section with 2 digit camber such as a NACA 2512-34 airfoil. The 1st digit is the maximum camber in percent chord. The 2nd digit is the chordwise location of maximum camber in tenths of chord. The next two digits are the airfoil thickness in percent chord. The 1st digit after the hyphen is the leading edge radius index and the last digit after the hyphen is the position of maximum thickness in tenths of chord.

Ported from FORTRAN "NACA4.FOR" to Java by: Joseph A. Huwaldt, October 20, 2000

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:  8Aug95  1.7   RLC

         NOTES - This program has been known by the names ANALIN, FOURDIGIT and NACA4.
         REFERENCES-  NASA Technical Memorandum TM X-3284 (November, 1975),
                      "Development of a Computer Program to Obtain Ordinates for
                      NACA 4-Digit, 4-Digit Modified, 5-Digit and 16-Digit Airfoils",
                      by Charles L. Ladson and Cuyler W. Brooks, Jr.,
                      NASA Langley Research Center.

                      NASA Technical Memorandum TM 4741 (December 1996),
                      "Computer Program to Obtain Ordinates for NACA Airfoils",
                      by Charles L. Ladson, Cuyler W. Brooks, Jr., and Acquilla S. Hill,
                      NASA Langley Research Center and
                      Darrell W. Sproles, Computer Sciences Corporation, Hampton, VA.

                      "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: October 20, 2000

See Also:

Serialized Form

Constructor Summary

Constructors

Constructor	Description
NACA4ModCambered(double thickness, double camber, double xcamber, double Rle, double xThickness, double length)	Create a cambered NACA modified 4 digit airfoil with the specified parameters.
NACA4ModCambered(double thickness, double camber, double xcamber, int LEindex, double xThickness, double length)	Create a cambered NACA modified 4 digit airfoil with the specified parameters.

Method Summary

Modifier and Type	Method	Description
static void	main(java.lang.String[] args)	Simple method to test this class.
java.lang.String	toString()	Returns a string representation of this airfoil (the NACA designation of this airfoil).

Methods inherited from class jahuwaldt.aero.airfoils.NACA4Uncambered

getCamber, getLower, getLowerYp, getUpper, getUpperYp

Methods inherited from class java.lang.Object

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

Constructor Detail

NACA4ModCambered

public NACA4ModCambered(double thickness,
                        double camber,
                        double xcamber,
                        double Rle,
                        double xThickness,
                        double length)

Create a cambered NACA modified 4 digit airfoil with the specified parameters. For example: a NACA 2512-34 airfoil translates to: thickness = 0.12, camber = 0.02, xcamber = 0.50, Rle = 0.003967, and xThickness = 0.40.

Parameters:

thickness - The thickness to chord ratio (e.g.: 0.09 ==> 9% t/c).

camber - The maximum camber ordinate-to-chord ratio (e.g.: 0.06 ==> 6% camber/c).

xcamber - The position of maximum camber in tenths of chord (e.g.: 0.40 ==> max camber at 4% chord).

Rle - The radius of the leading edge of the airfoil in percent chord.

xThickness - The position of maximum thickness in percent chord (e.g.: 0.40 => 40% t/c).

length - The chord length.

NACA4ModCambered

public NACA4ModCambered(double thickness,
                        double camber,
                        double xcamber,
                        int LEindex,
                        double xThickness,
                        double length)

Create a cambered NACA modified 4 digit airfoil with the specified parameters. For example: a NACA 2512-34 airfoil translates to: thickness = 0.12, camber = 0.02, xcamber = 0.50, LEindex = 3, xThickness = 0.40..

Parameters:

thickness - The thickness to chord ratio (e.g.: 0.09 ==> 9% t/c).

camber - The maximum camber ordinate-to-chord ratio (e.g.: 0.06 ==> 6% camber/c).

xcamber - The position of maximum camber in tenths of chord (e.g.: 0.40 ==> max camber at 4% chord).

LEindex - The leading edge radius index for this airfoil. Should be a number from 1 to 8.

xThickness - The position of maximum thickness in percent chord (e.g.: 0.40 => 40% t/c).

length - The chord length.

Method Detail

toString

public java.lang.String toString()

Returns a string representation of this airfoil (the NACA designation of this airfoil).

Overrides:

toString in class NACA4ModUncambered

main

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

Simple method to test this class.