public class NACA4ModUncambered extends NACA4Uncambered
This class represents an arbitrary uncambered NACA modified 4 digit airfoil section such as a NACA 0012-34 airfoil. The 1st two digits indicate a symmetric airfoil, the 2nd two, the thickness-chord ratio. 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 19, 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
Constructor and Description |
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NACA4ModUncambered(double thickness,
double Rle,
double xThickness,
double length)
Create an uncambered NACA modified 4 digit airfoil with the
specified parameters.
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NACA4ModUncambered(double thickness,
int LEindex,
double xThickness,
double length)
Create an uncambered NACA modified 4 digit airfoil with the
specified parameters.
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Modifier and Type | Method and Description |
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static void |
main(java.lang.String[] args)
Simple method to test this class.
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java.lang.String |
toString()
Returns a string representation of this airfoil
(the NACA designation of this airfoil).
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getCamber, getLower, getLowerYp, getUpper, getUpperYp
public NACA4ModUncambered(double thickness, double Rle, double xThickness, double length)
thickness
- The thickness to chord ratio (e.g.: 0.09 ==> 9% t/c).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.public NACA4ModUncambered(double thickness, int LEindex, double xThickness, double length)
thickness
- The thickness to chord ratio (e.g.: 0.09 ==> 9% t/c).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.public java.lang.String toString()
toString
in class NACA4Uncambered
public static void main(java.lang.String[] args)