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
Constructor and Description |
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NACA6ASeries(double CLi,
double thickness,
double length)
Create a NACA 6*A series airfoil with the specified parameters.
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Modifier and Type | Method and Description |
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protected boolean |
modCamberLine(double x,
boolean if6xa,
double ycmb,
double tanth,
double ycp2,
double cli,
double[] outputs)
Method used by 6*A series airfoils to modify the camber line.
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protected void |
modTrailingEdge(double x,
double xu,
double yu,
double xl,
double yl,
double[] outputs)
Method used by 6*A series airfoils to modify the airfoil trailing edge.
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getCamber, getLower, getLowerYp, getProfile, getUpper, getUpperYp, phep, phps, seval, spline, toString
public NACA6ASeries(double CLi, double thickness, double length)
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.protected final boolean modCamberLine(double x, boolean if6xa, double ycmb, double tanth, double ycp2, double cli, double[] outputs)
modCamberLine
in class NACA6Series
x
- The current x/c being calculated.if6xa
- Flag indicating if 6*A specific calculations have been enabled.ycmb
- The y position of the camber line.tanth
- The slope of the camber line.ycp2
- ?cli
- The design lift coefficient.outputs
- An existing 3-element array filled in with
outputs: outputs[ycmb, tanth, ycp2].protected final void modTrailingEdge(double x, double xu, double yu, double xl, double yl, double[] outputs)
modTrailingEdge
in class NACA6Series
x
- The x/c location being calculated.xu
- The x/c location of the upper surface ordinate.yu
- The upper surface ordinate.xl
- The x/c location of hte lower surface ordinate.yl
- The lower surface ordinate.outputs
- An existing 2-element array filled in with
outputs: outputs[yu, yl].