Package jahuwaldt.aero.airfoils

Class NACA4Uncambered

  • All Implemented Interfaces:
    Airfoil, java.io.Serializable
    Direct Known Subclasses:
    NACA4Cambered, NACA4ModUncambered, NACA5Cambered, NACA5Reflexed
    public class NACA4Uncambered
extends java.lang.Object
implements Airfoil

    This class represents an arbitrary uncambered NACA 4 digit airfoil section such as a NACA 0012 airfoil. The 1st two digits indicate a symmetric airfoil, the 2nd two, the thickness to chord ratio. All NACA 4 and 5 digit (and 16 series and mod-4 digit) airfoils inherit from this class the generic code for generating airfoil ordinates.

    Ported from FORTRAN "NACA4.FOR" to Java by: Joseph A. Huwaldt, October 8, 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:
    March 7, 2013
    Author:
    Joseph A. Huwaldt Date: October 8, 2000
    See Also:
    Serialized Form

    • Constructor Summary

      Constructors 
      Constructor Description
      NACA4Uncambered()
      Creates an uncambered NACA 4 digit airfoil with a thickness to chord ratio of 20% and a chord length of 1.0.
      NACA4Uncambered​(double thickness, double length)
      Create an uncambered NACA 4 digit airfoil with the specified parameters.

    • Method Summary

      All Methods Static Methods Instance Methods Concrete Methods 
      Modifier and Type Method Description
      java.util.List<java.awt.geom.Point2D> getCamber()
      Returns a list of points containing the camber line of the airfoil.
      java.util.List<java.awt.geom.Point2D> getLower()
      Returns a list of points containing the abscissas (X coordinate) and ordinates (Y coordinate) of the points defining the lower surface of the airfoil.
      java.util.List<java.lang.Double> getLowerYp()
      Returns a list containing the slope (dy/dx) of the lower surface of the airfoil at each ordinate.
      java.util.List<java.awt.geom.Point2D> getUpper()
      Returns a list of points containing the abscissas (X coordinate) and ordinates (Y coordinate) of the points defining the upper surface of the airfoil.
      java.util.List<java.lang.Double> getUpperYp()
      Returns a list containing the slope (dy/dx) of the upper surface of the airfoil at each ordinate.
      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 java.lang.Object

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

    • Constructor Detail

      • NACA4Uncambered

        public NACA4Uncambered()
        Creates an uncambered NACA 4 digit airfoil with a thickness to chord ratio of 20% and a chord length of 1.0.

      • NACA4Uncambered

        public NACA4Uncambered​(double thickness,
                       double length)
        Create an uncambered NACA 4 digit airfoil with the specified parameters.
        Parameters:
        thickness - The thickness to chord ratio (e.g.: 0.20 ==> 20% t/c).
        length - The chord length.

    • Method Detail

      • getUpper

        public java.util.List<java.awt.geom.Point2D> getUpper()
        Returns a list of points containing the abscissas (X coordinate) and ordinates (Y coordinate) of the points defining the upper surface of the airfoil.
        Specified by:
        getUpper in interface Airfoil

      • getLower

        public java.util.List<java.awt.geom.Point2D> getLower()
        Returns a list of points containing the abscissas (X coordinate) and ordinates (Y coordinate) of the points defining the lower surface of the airfoil.
        Specified by:
        getLower in interface Airfoil

      • getCamber

        public java.util.List<java.awt.geom.Point2D> getCamber()
        Returns a list of points containing the camber line of the airfoil.
        Specified by:
        getCamber in interface Airfoil

      • getUpperYp

        public java.util.List<java.lang.Double> getUpperYp()
        Returns a list containing the slope (dy/dx) of the upper surface of the airfoil at each ordinate.
        Specified by:
        getUpperYp in interface Airfoil

      • getLowerYp

        public java.util.List<java.lang.Double> getLowerYp()
        Returns a list containing the slope (dy/dx) of the lower surface of the airfoil at each ordinate.
        Specified by:
        getLowerYp in interface Airfoil

      • toString

        public java.lang.String toString()
        Returns a string representation of this airfoil (the NACA designation of this airfoil).
        Overrides:
        toString in class java.lang.Object

      • main

        public static void main​(java.lang.String[] args)
        Simple method to test this class.