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N

NACA4Cambered - Class in jahuwaldt.aero.airfoils
This class represents an arbitrary cambered NACA 4 digit airfoil section with 2 digit camber such as a NACA 6409 airfoil.
NACA4Cambered(double, double, double, double) - Constructor for class jahuwaldt.aero.airfoils.NACA4Cambered
Create a cambered NACA 4 digit airfoil with the specified parameters.
NACA4ModCambered - Class in jahuwaldt.aero.airfoils
This class represents an arbitrary cambered NACA modified 4 digit airfoil section with 2 digit camber such as a NACA 2512-34 airfoil.
NACA4ModCambered(double, double, double, double, double, double) - Constructor for class jahuwaldt.aero.airfoils.NACA4ModCambered
Create a cambered NACA modified 4 digit airfoil with the specified parameters.
NACA4ModCambered(double, double, double, int, double, double) - Constructor for class jahuwaldt.aero.airfoils.NACA4ModCambered
Create a cambered NACA modified 4 digit airfoil with the specified parameters.
NACA4ModUncambered - Class in jahuwaldt.aero.airfoils
This class represents an arbitrary uncambered NACA modified 4 digit airfoil section such as a NACA 0012-34 airfoil.
NACA4ModUncambered(double, double, double, double) - Constructor for class jahuwaldt.aero.airfoils.NACA4ModUncambered
Create an uncambered NACA modified 4 digit airfoil with the specified parameters.
NACA4ModUncambered(double, int, double, double) - Constructor for class jahuwaldt.aero.airfoils.NACA4ModUncambered
Create an uncambered NACA modified 4 digit airfoil with the specified parameters.
NACA4Uncambered - Class in jahuwaldt.aero.airfoils
This class represents an arbitrary uncambered NACA 4 digit airfoil section such as a NACA 0012 airfoil.
NACA4Uncambered() - Constructor for class jahuwaldt.aero.airfoils.NACA4Uncambered
Creates an uncambered NACA 4 digit airfoil with a thickness to chord ratio of 20% and a chord length of 1.0.
NACA4Uncambered(double, double) - Constructor for class jahuwaldt.aero.airfoils.NACA4Uncambered
Create an uncambered NACA 4 digit airfoil with the specified parameters.
NACA4Uncambered.Ordinate - Class in jahuwaldt.aero.airfoils
Class that serves as a simple container for airfoil ordinate data.
NACA4Uncambered.Ordinate() - Constructor for class jahuwaldt.aero.airfoils.NACA4Uncambered.Ordinate
 
NACA5Cambered - Class in jahuwaldt.aero.airfoils
This class represents an arbitrary cambered unreflexed NACA 5 digit airfoil section with 3 digit camber such as a NACA 23012 airfoil.
NACA5Cambered(double, double, double, double, double) - Constructor for class jahuwaldt.aero.airfoils.NACA5Cambered
Create a cambered unreflexed NACA 5 digit airfoil with the specified parameters.
NACA5Cambered(double, int, double) - Constructor for class jahuwaldt.aero.airfoils.NACA5Cambered
Create a cambered unreflexed NACA 5 digit airfoil with the specified parameters.
NACA5Reflexed - Class in jahuwaldt.aero.airfoils
This class represents an arbitrary cambered, reflexed, NACA 5 digit airfoil section with 3 digit camber such as a NACA 23112 airfoil.
NACA5Reflexed(double, double, double, double, double, double) - Constructor for class jahuwaldt.aero.airfoils.NACA5Reflexed
Create a cambered reflexed NACA 5 digit airfoil with the specified parameters.
NACA5Reflexed(double, int, double) - Constructor for class jahuwaldt.aero.airfoils.NACA5Reflexed
Create a cambered reflexed NACA 5 digit airfoil with the specified parameters.
NACA63ASeries - Class in jahuwaldt.aero.airfoils
This class represents an arbitrary NACA 63A series airfoil section such as a NACA 63A020 airfoil.
NACA63ASeries(double, double, double) - Constructor for class jahuwaldt.aero.airfoils.NACA63ASeries
Create a NACA 63A series airfoil with the specified parameters.
NACA63Series - Class in jahuwaldt.aero.airfoils
This class represents an arbitrary NACA 63 series airfoil section such as a NACA 63-020 airfoil.
NACA63Series(double, double, double) - Constructor for class jahuwaldt.aero.airfoils.NACA63Series
Create a NACA 63 series airfoil with the specified parameters.
NACA64ASeries - Class in jahuwaldt.aero.airfoils
This class represents an arbitrary NACA 64A series airfoil section such as a NACA 64A020 airfoil.
NACA64ASeries(double, double, double) - Constructor for class jahuwaldt.aero.airfoils.NACA64ASeries
Create a NACA 64A series airfoil with the specified parameters.
NACA64Series - Class in jahuwaldt.aero.airfoils
This class represents an arbitrary NACA 64 series airfoil section such as a NACA 64-020 airfoil.
NACA64Series(double, double, double) - Constructor for class jahuwaldt.aero.airfoils.NACA64Series
Create a NACA 64 series airfoil with the specified parameters.
NACA65ASeries - Class in jahuwaldt.aero.airfoils
This class represents an arbitrary NACA 65A series airfoil section such as a NACA 65A020 airfoil.
NACA65ASeries(double, double, double) - Constructor for class jahuwaldt.aero.airfoils.NACA65ASeries
Create a NACA 65A series airfoil with the specified parameters.
NACA65Series - Class in jahuwaldt.aero.airfoils
This class represents an arbitrary NACA 65 series airfoil section such as a NACA 65-020 airfoil.
NACA65Series(double, double, double) - Constructor for class jahuwaldt.aero.airfoils.NACA65Series
Create a NACA 65 series airfoil with the specified parameters.
NACA66Series - Class in jahuwaldt.aero.airfoils
This class represents an arbitrary NACA 66 series airfoil section such as a NACA 66-020 airfoil.
NACA66Series(double, double, double) - Constructor for class jahuwaldt.aero.airfoils.NACA66Series
Create a NACA 66 series airfoil with the specified parameters.
NACA67Series - Class in jahuwaldt.aero.airfoils
This class represents an arbitrary NACA 67 series airfoil section such as a NACA 67-020 airfoil.
NACA67Series(double, double, double) - Constructor for class jahuwaldt.aero.airfoils.NACA67Series
Create a NACA 67 series airfoil with the specified parameters.
NACA6ASeries - Class in jahuwaldt.aero.airfoils
This class represents an arbitrary NACA 6*A series airfoil section such as a NACA 63A-020 airfoil.
NACA6ASeries(double, double, double) - Constructor for class jahuwaldt.aero.airfoils.NACA6ASeries
Create a NACA 6*A series airfoil with the specified parameters.
NACA6Series - Class in jahuwaldt.aero.airfoils
This class represents an arbitrary NACA 6 or 6*A series airfoil section such as a NACA 63-020 airfoil.
NACA6Series(double, double, double) - Constructor for class jahuwaldt.aero.airfoils.NACA6Series
Create a NACA 6 series airfoil with the specified parameters.
NACAFactory - Class in jahuwaldt.aero.airfoils
This class contains a method for parsing a NACA airfoil designation string (such as "NACA 2312") and returning a corresponding Airfoil object.
NACAFactory() - Constructor for class jahuwaldt.aero.airfoils.NACAFactory
 
NASAReader - Class in jahuwaldt.tools.tables
A class that provides methods for reading or writing a NASA 2, 3, or 4 argument multi-table file.
NASAReader() - Constructor for class jahuwaldt.tools.tables.NASAReader
 
networks() - Method in class jahuwaldt.aero.panelgeom.GeomComponent
Return an enumeration of all the networks in this component.
nextLine(StreamTokenizer) - Static method in class jahuwaldt.tools.tables.TRUtils
Skips to the start of the next line of the supplied input stream.
nextNumber(StreamTokenizer) - Static method in class jahuwaldt.tools.tables.TRUtils
Read in the next numeric value from a stream tokenizer.
nextWord(StreamTokenizer) - Static method in class jahuwaldt.tools.tables.TRUtils
Read in the next string value from a stream tokenizer.
NO - Static variable in interface jahuwaldt.tools.tables.FTableReader
Constant indicating that a reader can not read a specified file.
ns_CpMax(double, double) - Static method in class jahuwaldt.aero.ShockMethods
Calculates the maximum pressure coefficient behind a normal shock.
ns_M2(double, double) - Static method in class jahuwaldt.aero.ShockMethods
Calculates the Mach number downstream of a normal shock.
ns_P2P1(double, double) - Static method in class jahuwaldt.aero.ShockMethods
Calculates the pressure ratio across a normal shock.
ns_PT2P1(double, double) - Static method in class jahuwaldt.aero.ShockMethods
Calculates the ratio of the total or stagnation pressure behind a normal shock divided by the static pressure before the shock.
ns_PT2PT1(double, double) - Static method in class jahuwaldt.aero.ShockMethods
Calculates the total or stagnation pressure ratio across a normal shock.
ns_PT2PT1(double, double, double) - Static method in class jahuwaldt.aero.ShockMethods
Calculates the total or stagnation pressure ratio across a normal shock.
ns_rho2rho1(double, double) - Static method in class jahuwaldt.aero.ShockMethods
Calculates the density ratio across a normal shock.
ns_T2T1(double, double) - Static method in class jahuwaldt.aero.ShockMethods
Calculates the temperature ratio across a normal shock.
numberOfNotes() - Method in class jahuwaldt.tools.tables.FloatTable
Returns the number of notes associated with this table.
numberOfNotes() - Method in class jahuwaldt.tools.tables.FTableDatabase
Returns the number of notes associated with this table database.
numDims - Variable in class jahuwaldt.tools.tables.FloatArrayNDim
e The number of dimensions that this array has.
numDims - Variable in class jahuwaldt.tools.tables.FloatTable
The number of dimensions of the data in this table.
numElements - Variable in class jahuwaldt.tools.tables.FloatArrayNDim
The total number of data values or elements.
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