Package jahuwaldt.aero.airfoils

Class NACA6ASeries

java.lang.Object

jahuwaldt.aero.airfoils.NACA6Series

jahuwaldt.aero.airfoils.NACA6ASeries

All Implemented Interfaces:

Airfoil, java.io.Serializable

Direct Known Subclasses:

NACA63ASeries, NACA64ASeries, NACA65ASeries

public abstract class NACA6ASeries
extends NACA6Series

This class represents an arbitrary NACA 6*A series airfoil section such as a NACA 63A-020 airfoil.

Ported from FORTRAN "NACA6.FOR" to Java by: Joseph A. Huwaldt, June 3, 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:

March 7, 2013

Author:

Joseph A. Huwaldt Date: June 5, 2010

See Also:

Serialized Form

Constructor Summary

Constructors

Constructor	Description
NACA6ASeries(double CLi, double thickness, double length)	Create a NACA 6*A series airfoil with the specified parameters.

Method Summary

Methods inherited from class jahuwaldt.aero.airfoils.NACA6Series

getCamber, getLower, getLowerYp, getProfile, getUpper, getUpperYp, toString

Methods inherited from class java.lang.Object

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

Constructor Detail

NACA6ASeries

public NACA6ASeries(double CLi,
                    double thickness,
                    double length)

Create a NACA 6*A series airfoil with the specified parameters.

Parameters:

CLi - Design lift coefficient (e.g.: 63A-206 has CLi = 0.2).

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

length - The chord length.