Package jahuwaldt.aero.airfoils

Class NACA5Reflexed

  • All Implemented Interfaces:
    Airfoil, java.io.Serializable
    public class NACA5Reflexed
extends NACA4Uncambered

    This class represents an arbitrary cambered, reflexed, NACA 5 digit airfoil section with 3 digit camber such as a NACA 23112 airfoil. The 1st digit is defined as 2/3 of the design lift coefficient (in tenths, i.e.: 2 denotes cl = 0.3). The 2nd digit is twice the chordwise location of maximum camber in tenths of chord. The 3rd digit of one indicates a reflexed trailing edge and the last two digits indicate the thickness ratio in percent chord.

    Ported from FORTRAN "NACA4.FOR" to Java by: Joseph A. Huwaldt, October 11, 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:
    February 22, 2025
    Author:
    Joseph A. Huwaldt Date: October 11, 2000
    See Also:
    Serialized Form

    • Constructor Summary

      Constructors 
      Constructor Description
      NACA5Reflexed​(double thickness, double k1, double k2ok1, double r, double xcamber, double length)
      Create a cambered reflexed NACA 5 digit airfoil with the specified parameters.
      NACA5Reflexed​(double thickness, int code, double length)
      Create a cambered reflexed NACA 5 digit airfoil with the specified parameters.

    • Constructor Detail

      • NACA5Reflexed

        public NACA5Reflexed​(double thickness,
                     double k1,
                     double k2ok1,
                     double r,
                     double xcamber,
                     double length)
        Create a cambered reflexed NACA 5 digit airfoil with the specified parameters. For example: a NACA 23112 airfoil translates to: thickness = 0.12, cl*2/3 = 2, xcamber*2 = 0.30. The 3rd digit must be 1 for a reflexed airfoil. This constructor requires the user to specify the 5 digit airfoil k and r factors and position of max camber explicitly. See NASA TM X-3284.
        Parameters:
        thickness - The thickness to chord ratio (e.g.: 0.09 == 9% t/c).
        k1 - The airfoil camber k1 factor as described in NASA TM X-3284.
        k2ok1 - The ratio of the k2 to k1 camber factors as described in NASA TM X-3284.
        r - The airfoil camber r factor as described in NASA TM X-3284.
        xcamber - The position of maximum camber in tenths of chord (e.g.: 0.40 == max camber at 4% chord).
        length - The chord length.

      • NACA5Reflexed

        public NACA5Reflexed​(double thickness,
                     int code,
                     double length)
        Create a cambered reflexed NACA 5 digit airfoil with the specified parameters. For example: a NACA 23112 airfoil translates to: thickness = 0.12, cl*2/3 = 2, xcamber*2 = 0.30. The 3rd digit must be 1 for a reflexed airfoil. This constructor requires the thickness and camber code (the 1st 2 digits of the airfoil designation).
        Parameters:
        thickness - The thickness to chord ratio (e.g.: 0.09 == 9% t/c).
        code - The 1st 2 digits of the airfoil designation. Acceptable values are: 22, 23, 24, and 25.
        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 NACA4Uncambered

      • main

        public static void main​(java.lang.String[] args)
        Simple method to test this class.
        Parameters:
        args - the command-line arguments