public class NACA5Cambered extends NACA4Uncambered
This class represents an arbitrary cambered unreflexed NACA 5 digit airfoil section with 3 digit camber such as a NACA 23012 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 zero indicates a non-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 9, 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
NACA4Uncambered.Ordinate
Constructor and Description |
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NACA5Cambered(double thickness,
double k1,
double r,
double xcamber,
double length)
Create a cambered unreflexed NACA 5 digit airfoil with the
specified parameters.
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NACA5Cambered(double thickness,
int code,
double length)
Create a cambered unreflexed NACA 5 digit airfoil with the
specified parameters.
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Modifier and Type | Method and Description |
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protected double |
calcCamber(double x,
NACA4Uncambered.Ordinate o)
Method to calculate the camber distribution for the airfoil.
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protected void |
calcLESlope(NACA4Uncambered.Ordinate o)
Method to determine the local slope of the airfoil at
the leading edge.
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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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calcOrdinateAft, calcOrdinateForward, getCamber, getLower, getLowerYp, getUpper, getUpperYp
public NACA5Cambered(double thickness, double k1, double r, double xcamber, double length)
thickness
- The thickness to chord ratio (e.g.: 0.09 ==> 9% t/c).k1
- The airfoil camber k factor 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.public NACA5Cambered(double thickness, int code, double length)
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: 21, 22, 23, 24, and 25.length
- The chord length.public java.lang.String toString()
toString
in class NACA4Uncambered
protected void calcLESlope(NACA4Uncambered.Ordinate o)
calcLESlope
in class NACA4Uncambered
o
- The ordinate data structure. The following are set: tanth, yp, ypp.protected double calcCamber(double x, NACA4Uncambered.Ordinate o)
calcCamber
in class NACA4Uncambered
x
- The x/c location currently being calculated.o
- The ordinate data structure. The following are set: yCMB, tanth, thp.public static void main(java.lang.String[] args)