Package | Description |
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jahuwaldt.aero.airfoils |
Modifier and Type | Method and Description |
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protected double |
NACA4Cambered.calcCamber(double x,
NACA4Uncambered.Ordinate o)
Method to calculate the camber distribution for the airfoil.
|
protected double |
NACA4ModCambered.calcCamber(double x,
NACA4Uncambered.Ordinate o)
Method to calculate the camber distribution for the airfoil.
|
protected double |
NACA4Uncambered.calcCamber(double x,
NACA4Uncambered.Ordinate o)
Method to calculate the camber distribution for the airfoil.
|
protected double |
NACA5Cambered.calcCamber(double x,
NACA4Uncambered.Ordinate o)
Method to calculate the camber distribution for the airfoil.
|
protected double |
NACA5Reflexed.calcCamber(double x,
NACA4Uncambered.Ordinate o)
Method to calculate the camber distribution for the airfoil.
|
protected void |
NACA4Cambered.calcLESlope(NACA4Uncambered.Ordinate o)
Method to determine the local slope of the airfoil at
the leading edge.
|
protected void |
NACA4ModCambered.calcLESlope(NACA4Uncambered.Ordinate o)
Method to determine the local slope of the airfoil at
the leading edge.
|
protected void |
NACA4Uncambered.calcLESlope(NACA4Uncambered.Ordinate o)
Method to determine the local slope of the airfoil at
the leading edge.
|
protected void |
NACA5Cambered.calcLESlope(NACA4Uncambered.Ordinate o)
Method to determine the local slope of the airfoil at
the leading edge.
|
protected void |
NACA5Reflexed.calcLESlope(NACA4Uncambered.Ordinate o)
Method to determine the local slope of the airfoil at
the leading edge.
|
protected void |
NACA4ModUncambered.calcOrdinateAft(double x,
NACA4Uncambered.Ordinate o)
Method to calculate the ordinates of the uncambered airfoil
aft of the maximum thickness point.
|
protected void |
NACA4Uncambered.calcOrdinateAft(double x,
NACA4Uncambered.Ordinate o)
Method to calculate the ordinate of the uncambered airfoil
aft of the maximum thickness point.
|
protected void |
NACA4ModUncambered.calcOrdinateForward(double x,
NACA4Uncambered.Ordinate o)
Method to calculate the ordinates of the uncambered airfoil
forward of the maximum thickness point.
|
protected void |
NACA4Uncambered.calcOrdinateForward(double x,
NACA4Uncambered.Ordinate o)
Method to calculate the ordinate of the uncambered airfoil
forward of the maximum thickness point.
|