- 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.