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M

M_fn_delta_VC(double, double, double) - Static method in class jahuwaldt.aero.Airspeeds
Method that calculates Mach number as a function of pressure ratio, and calibrated airspeed.
M_fn_VT_a(double, double) - Static method in class jahuwaldt.aero.Airspeeds
Calculates the Mach number as a function of the true airspeed and local speed of sound.
machAngle(double) - Static method in class jahuwaldt.aero.ShockMethods
Calculates the angle of a Mach wave with respect to the direction of motion (Mach angle).
main(String[]) - Static method in class jahuwaldt.aero.AeroCoefXAft
A simple method to test the methods in this class.
main(String[]) - Static method in class jahuwaldt.aero.AeroMethods
A simple method to test the methods in this class.
main(String[]) - Static method in class jahuwaldt.aero.airfoils.NACA4Cambered
Simple method to test this class.
main(String[]) - Static method in class jahuwaldt.aero.airfoils.NACA4ModCambered
Simple method to test this class.
main(String[]) - Static method in class jahuwaldt.aero.airfoils.NACA4ModUncambered
Simple method to test this class.
main(String[]) - Static method in class jahuwaldt.aero.airfoils.NACA4Uncambered
Simple method to test this class.
main(String[]) - Static method in class jahuwaldt.aero.airfoils.NACA5Cambered
Simple method to test this class.
main(String[]) - Static method in class jahuwaldt.aero.airfoils.NACA5Reflexed
Simple method to test this class.
main(String[]) - Static method in class jahuwaldt.aero.airfoils.NACA63ASeries
Simple method to test this class.
main(String[]) - Static method in class jahuwaldt.aero.airfoils.NACA63Series
Simple method to test this class.
main(String[]) - Static method in class jahuwaldt.aero.airfoils.NACA64ASeries
Simple method to test this class.
main(String[]) - Static method in class jahuwaldt.aero.airfoils.NACA64Series
Simple method to test this class.
main(String[]) - Static method in class jahuwaldt.aero.airfoils.NACA65ASeries
Simple method to test this class.
main(String[]) - Static method in class jahuwaldt.aero.airfoils.NACA65Series
Simple method to test this class.
main(String[]) - Static method in class jahuwaldt.aero.airfoils.NACA66Series
Simple method to test this class.
main(String[]) - Static method in class jahuwaldt.aero.airfoils.NACA67Series
Simple method to test this class.
main(String[]) - Static method in class jahuwaldt.aero.airfoils.NACAFactory
A simple method to test this class.
main(String[]) - Static method in class jahuwaldt.aero.ConicalShock
A simple method to test the methods in this class.
main(String[]) - Static method in class jahuwaldt.aero.Isentropic
A simple method to test the isentropic methods in this class.
main(String[]) - Static method in class jahuwaldt.aero.ShockMethods
A simple method to test the shock methods in this class.
main(String[]) - Static method in class jahuwaldt.aero.StdAtmos1962
A simple method to test the 1962 standard atmosphere.
main(String[]) - Static method in class jahuwaldt.aero.StdAtmos1976
A simple method to test the 1976 standard atmosphere.
main(String[]) - Static method in class jahuwaldt.util.ExponentialFormat
A simple static method to test this class.
main(String[]) - Static method in class jahuwaldt.util.GeneralFormat
A simple static method to test this class.
maxAltitude() - Method in class jahuwaldt.aero.StdAtmos
Returns the maximum altitude supported by this atmosphere model.
maxAltitude() - Method in class jahuwaldt.aero.StdAtmos1962
Returns the maximum altitude supported by this atmosphere model.
maxAltitude() - Method in class jahuwaldt.aero.StdAtmos1976
Returns the maximum altitude supported by this atmosphere model in meters.
MAYBE - Static variable in interface jahuwaldt.tools.tables.FTableReader
Constant indicating that a reader might be able to read a specified file, but can't determine for sure.
Mcr(double, double, double) - Static method in class jahuwaldt.aero.AeroMethods
Estimates the critical Mach number given the minimum incompressible pressure coefficient.
Me(double, double, double, boolean) - Static method in class jahuwaldt.aero.Isentropic
Calculates the Mach number at the entrance or exit of a duct (nozzle) given the ratio of the local duct area at the entrance or exit to the area where the sonic (M=1) condition exists.
Me(double, double, double, boolean, IsentropicMeEvaluator) - Static method in class jahuwaldt.aero.Isentropic
Calculates the Mach number at the entrance or exit of a duct (nozzle) given the ratio of the local duct area at the entrance or exit to the area where the sonic (M=1) condition exists.
minAltitude() - Method in class jahuwaldt.aero.StdAtmos
Returns the minimum altitude supported by this atmosphere model.
minAltitude() - Method in class jahuwaldt.aero.StdAtmos1962
Returns the minimum altitude supported by this atmosphere model.
minAltitude() - Method in class jahuwaldt.aero.StdAtmos1976
Returns the minimum altitude supported by this atmosphere model in meters.
modCamberLine(double, boolean, double, double, double, double, double[]) - Method in class jahuwaldt.aero.airfoils.NACA6ASeries
Method used by 6*A series airfoils to modify the camber line.
modCamberLine(double, boolean, double, double, double, double, double[]) - Method in class jahuwaldt.aero.airfoils.NACA6Series
Method used by 6*A series airfoils to modify the camber line.
modTrailingEdge(double, double, double, double, double, double[]) - Method in class jahuwaldt.aero.airfoils.NACA6ASeries
Method used by 6*A series airfoils to modify the airfoil trailing edge.
modTrailingEdge(double, double, double, double, double, double[]) - Method in class jahuwaldt.aero.airfoils.NACA6Series
Method used by 6*A series airfoils to modify the airfoil trailing edge.
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