dynamics.models.uav

Class USStandardAtmosphere1976

java.lang.Object

dynamics.models.uav.USStandardAtmosphere1976

public class USStandardAtmosphere1976
extends Object

Constructor Summary

Constructors

Constructor and Description
USStandardAtmosphere1976()

Method Summary

Modifier and Type	Method and Description
static double	densityAtAltitude(double altitude) Computes the air density (rho) at a specified altitude (assumes dry air)
static double	dynamicPressureAtAltitude(double altitude, double v) Computes the dynamic pressure of the airfoil given a velocity vector
static double	machNumber(double altitude, double velocity) Computes the mach number at a specified altitude for a specified velocity
static double	pressureAtAltitude(double altitude) Computes the air pressure at a specified altitude Formula assumes dry air and utilizes equations available at http://www.atmosphere.mpg.de/enid/16h.html
static double	speedOfSound(double altitude) Computes the speed of sound at a specified altitude
static double	temperatureAtAltitude(double altitude) Computes the temperature (degrees K) at a specified altitude based on a standard day 101325.0 mbar (29.92" Hg) and 288.15 deg K (15C) at mean sea level)

Methods inherited from class java.lang.Object

clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait

Constructor Detail

USStandardAtmosphere1976

public USStandardAtmosphere1976()

Method Detail

temperatureAtAltitude

public static double temperatureAtAltitude(double altitude)

Computes the temperature (degrees K) at a specified altitude based on a standard day 101325.0 mbar (29.92" Hg) and 288.15 deg K (15C) at mean sea level)

Parameters:

altitude - meters above mean sea level

Returns:

degrees Kelvin

speedOfSound

public static double speedOfSound(double altitude)

Computes the speed of sound at a specified altitude

Parameters:

altitude - meters above sea level

Returns:

meters per second

machNumber

public static double machNumber(double altitude,
                                double velocity)

Computes the mach number at a specified altitude for a specified velocity

Parameters:

altitude - meters above sea level

velocity - meters per second

Returns:

dimensionless mach number

pressureAtAltitude

public static double pressureAtAltitude(double altitude)

Computes the air pressure at a specified altitude Formula assumes dry air and utilizes equations available at http://www.atmosphere.mpg.de/enid/16h.html

Parameters:

altitude - meters above mean sea level

Returns:

pressure in Pascals (mb * 100)

densityAtAltitude

public static double densityAtAltitude(double altitude)

Computes the air density (rho) at a specified altitude (assumes dry air)

Parameters:

altitude - meters above mean sea level

Returns:

air density in kilograms per meter cubed

dynamicPressureAtAltitude

public static double dynamicPressureAtAltitude(double altitude,
                                               double v)

Computes the dynamic pressure of the airfoil given a velocity vector

Parameters:

altitude - meters mean sea level

v - scalar velocity in meters per second

Returns:

dynamic pressure