Encapsulates various uncategorized scheduled functions. More...

#include <FGAuxiliary.h>

Inheritance diagram for FGAuxiliary:

Collaboration diagram for FGAuxiliary:

Classes
struct	Inputs

Public Member Functions
	FGAuxiliary (FGFDMExec *Executive)
	Constructor. More...

	~FGAuxiliary ()
	Destructor.

double	Getadot (void) const

double	Getadot (int unit) const

double	GetAeroPQR (int axis) const

const FGColumnVector3 &	GetAeroPQR (void) const

const FGColumnVector3 &	GetAeroUVW (void) const

double	GetAeroUVW (int idx) const

double	Getalpha (void) const

double	Getalpha (int unit) const

double	Getbdot (void) const

double	Getbdot (int unit) const

double	Getbeta (void) const

double	Getbeta (int unit) const

double	GetCrossWind (void) const

int	GetDayOfYear (void) const

double	GetDistanceRelativePosition (void) const

double	GetEulerRates (int axis) const

const FGColumnVector3 &	GetEulerRates (void) const

double	GetGamma (void) const

double	GetGroundTrack (void) const

double	GetHeadWind (void) const

double	GetHOverBCG (void) const

double	GetHOverBMAC (void) const

double	GethVRP (void) const

double	GetLatitudeRelativePosition (void) const

const FGLocation &	GetLocationVRP (void) const

double	GetLongitudeRelativePosition (void) const

double	GetMach (void) const
	Gets the Mach number. More...

double	GetMachU (void) const
	The mach number calculated using the vehicle X axis velocity. More...

double	GetMagBeta (void) const

double	GetMagBeta (int unit) const

const FGColumnVector3 &	GetNcg (void) const

double	GetNcg (int idx) const

double	GetNlf (void) const

double	GetNpilot (int idx) const

const FGColumnVector3 &	GetNpilot (void) const

const FGColumnVector3 &	GetNwcg (void) const

double	GetNy (void) const
	The lateral acceleration in g's of the aircraft center of gravity. More...

double	GetNz (void) const
	The vertical acceleration in g's of the aircraft center of gravity. More...

double	GetPilotAccel (int idx) const

const FGColumnVector3 &	GetPilotAccel (void) const

double	Getqbar (void) const

double	GetqbarUV (void) const

double	GetqbarUW (void) const

double	GetReynoldsNumber (void) const

double	GetSecondsInDay (void) const

double	GetTAT_C (void) const

const FGMatrix33 &	GetTb2w (void)
	Calculates and returns the body-to-wind axis transformation matrix. More...

double	GetTotalPressure (void) const
	Returns the total pressure. More...

double	GetTotalTemperature (void) const
	Returns the total temperature. More...

const FGMatrix33 &	GetTw2b (void)
	Calculates and returns the wind-to-body axis transformation matrix. More...

double	GetVcalibratedFPS (void) const
	Returns Calibrated airspeed in feet/second. More...

double	GetVcalibratedKTS (void) const
	Returns Calibrated airspeed in knots. More...

double	GetVequivalentFPS (void) const
	Returns equivalent airspeed in feet/second. More...

double	GetVequivalentKTS (void) const
	Returns equivalent airspeed in knots. More...

double	GetVground (void) const
	Gets the ground speed in feet per second. More...

double	GetVt (void) const
	Gets the magnitude of total vehicle velocity including wind effects in feet per second. More...

double	GetVtrueFPS () const
	Returns the true airspeed in feet per second. More...

double	GetVtrueKTS () const
	Returns the true airspeed in knots. More...

bool	InitModel (void)

bool	Run (bool Holding)
	Runs the Auxiliary routines; called by the Executive Can pass in a value indicating if the executive is directing the simulation to Hold. More...

void	SetAeroPQR (const FGColumnVector3 &tt)

void	SetDayOfYear (int doy)

void	SetSecondsInDay (double sid)

Public Member Functions inherited from FGModel
	FGModel (FGFDMExec *)
	Constructor.

virtual	~FGModel ()
	Destructor.

virtual SGPath	FindFullPathName (const SGPath &path) const

FGFDMExec *	GetExec (void)

unsigned int	GetRate (void)
	Get the output rate for the model in frames.

void	SetPropertyManager (FGPropertyManager *fgpm)

void	SetRate (unsigned int tt)
	Set the ouput rate for the model in frames.

Public Member Functions inherited from FGModelFunctions
std::string	GetFunctionStrings (const std::string &delimeter) const
	Gets the strings for the current set of functions. More...

std::string	GetFunctionValues (const std::string &delimeter) const
	Gets the function values. More...

FGFunction *	GetPreFunction (const std::string &name)
	Get one of the "pre" function. More...

bool	Load (Element el, FGPropertyManager PropertyManager, std::string prefix="")

void	PostLoad (Element el, FGPropertyManager PropertyManager, std::string prefix="")

void	PreLoad (Element el, FGPropertyManager PropertyManager, std::string prefix="")

void	RunPostFunctions (void)

void	RunPreFunctions (void)

Public Member Functions inherited from FGJSBBase
	FGJSBBase ()
	Constructor for FGJSBBase.

virtual	~FGJSBBase ()
	Destructor for FGJSBBase.

void	disableHighLighting (void)
	Disables highlighting in the console output.

std::string	GetVersion (void)
	Returns the version number of JSBSim. More...

void	PutMessage (const Message &msg)
	Places a Message structure on the Message queue. More...

void	PutMessage (const std::string &text)
	Creates a message with the given text and places it on the queue. More...

void	PutMessage (const std::string &text, bool bVal)
	Creates a message with the given text and boolean value and places it on the queue. More...

void	PutMessage (const std::string &text, int iVal)
	Creates a message with the given text and integer value and places it on the queue. More...

void	PutMessage (const std::string &text, double dVal)
	Creates a message with the given text and double value and places it on the queue. More...

int	SomeMessages (void)
	Reads the message on the queue (but does not delete it). More...

void	ProcessMessage (void)
	Reads the message on the queue and removes it from the queue. More...

Message *	ProcessNextMessage (void)
	Reads the next message on the queue and removes it from the queue. More...

Public Attributes
struct JSBSim::FGAuxiliary::Inputs	in

Public Attributes inherited from FGModel
std::string	Name

Additional Inherited Members
Public Types inherited from FGJSBBase
enum	{ eL = 1, eM, eN }
	Moments L, M, N.

enum	{ eP = 1, eQ, eR }
	Rates P, Q, R.

enum	{ eU = 1, eV, eW }
	Velocities U, V, W.

enum	{ eX = 1, eY, eZ }
	Positions X, Y, Z.

enum	{ ePhi = 1, eTht, ePsi }
	Euler angles Phi, Theta, Psi.

enum	{ eDrag = 1, eSide, eLift }
	Stability axis forces, Drag, Side force, Lift.

enum	{ eRoll = 1, ePitch, eYaw }
	Local frame orientation Roll, Pitch, Yaw.

enum	{ eNorth = 1, eEast, eDown }
	Local frame position North, East, Down.

enum	{ eLat = 1, eLong, eRad }
	Locations Radius, Latitude, Longitude.

enum	{ inNone = 0, inDegrees, inRadians, inMeters, inFeet }
	Conversion specifiers.

Static Public Member Functions inherited from FGJSBBase
static double	CelsiusToFahrenheit (double celsius)
	Converts from degrees Celsius to degrees Fahrenheit. More...

static double	CelsiusToKelvin (double celsius)
	Converts from degrees Celsius to degrees Kelvin. More...

static double	CelsiusToRankine (double celsius)
	Converts from degrees Celsius to degrees Rankine. More...

static double	Constrain (double min, double value, double max)
	Constrain a value between a minimum and a maximum value.

static bool	EqualToRoundoff (double a, double b)
	Finite precision comparison. More...

static bool	EqualToRoundoff (float a, float b)
	Finite precision comparison. More...

static bool	EqualToRoundoff (float a, double b)
	Finite precision comparison. More...

static bool	EqualToRoundoff (double a, float b)
	Finite precision comparison. More...

static double	FahrenheitToCelsius (double fahrenheit)
	Converts from degrees Fahrenheit to degrees Celsius. More...

static double	FeetToMeters (double measure)
	Converts from feet to meters. More...

static double	GaussianRandomNumber (void)

static double	KelvinToCelsius (double kelvin)
	Converts from degrees Kelvin to degrees Celsius. More...

static double	KelvinToFahrenheit (double kelvin)
	Converts from degrees Kelvin to degrees Fahrenheit. More...

static double	KelvinToRankine (double kelvin)
	Converts from degrees Kelvin to degrees Rankine. More...

static double	MachFromVcalibrated (double vcas, double p, double psl, double rhosl)
	Calculate the Mach number from the calibrated airspeed. More...

static double	PitotTotalPressure (double mach, double p)
	Compute the total pressure in front of the Pitot tube. More...

static double	RankineToCelsius (double rankine)
	Converts from degrees Rankine to degrees Celsius. More...

static double	RankineToKelvin (double rankine)
	Converts from degrees Rankine to degrees Kelvin. More...

static double	sign (double num)

static double	VcalibratedFromMach (double mach, double p, double psl, double rhosl)
	Calculate the calibrated airspeed from the Mach number. More...

Static Public Attributes inherited from FGJSBBase
static short	debug_lvl = 1

static char	highint [5] = {27, '[', '1', 'm', '\0' }
	highlights text

static char	halfint [5] = {27, '[', '2', 'm', '\0' }
	low intensity text

static char	normint [6] = {27, '[', '2', '2', 'm', '\0' }
	normal intensity text

static char	reset [5] = {27, '[', '0', 'm', '\0' }
	resets text properties

static char	underon [5] = {27, '[', '4', 'm', '\0' }
	underlines text

static char	underoff [6] = {27, '[', '2', '4', 'm', '\0' }
	underline off

static char	fgblue [6] = {27, '[', '3', '4', 'm', '\0' }
	blue text

static char	fgcyan [6] = {27, '[', '3', '6', 'm', '\0' }
	cyan text

static char	fgred [6] = {27, '[', '3', '1', 'm', '\0' }
	red text

static char	fggreen [6] = {27, '[', '3', '2', 'm', '\0' }
	green text

static char	fgdef [6] = {27, '[', '3', '9', 'm', '\0' }
	default text

Protected Member Functions inherited from FGModel
virtual bool	Load (Element *el)
	Loads this model. More...

Protected Member Functions inherited from FGJSBBase
void	Debug (int)

Static Protected Member Functions inherited from FGJSBBase
static std::string	CreateIndexedPropertyName (const std::string &Property, int index)

Protected Attributes inherited from FGModel
unsigned int	exe_ctr

FGFDMExec *	FDMExec

FGPropertyManager *	PropertyManager

unsigned int	rate

Protected Attributes inherited from FGModelFunctions
FGPropertyReader	LocalProperties

std::vector< FGFunction * >	PostFunctions

std::vector< FGFunction * >	PreFunctions

Static Protected Attributes inherited from FGJSBBase
static const double	degtorad = 0.017453292519943295769236907684886

static const double	fpstokts = 1.0/ktstofps

static const double	fttom = 0.3048

static int	gaussian_random_number_phase = 0

static const double	hptoftlbssec = 550.0

static const double	in3tom3 = 1.638706E-5

static const double	inchtoft = 0.08333333

static const double	inhgtopa = 3386.38

static const std::string	JSBSim_version = "1.0 " __DATE__ " " __TIME__

static const double	kgtolb = 2.20462

static const double	kgtoslug = 0.06852168

static const double	ktstofps = 1.68781

static const double	lbtoslug = 1.0/slugtolb

static Message	localMsg

static const double	m3toft3 = 1.0/(fttomfttomfttom)

static double	Mair = 28.9645

static unsigned int	messageId = 0

static std::queue< Message >	Messages

static const std::string	needed_cfg_version = "2.0"

static const double	psftoinhg = 0.014138

static const double	psftopa = 47.88

static const double	radtodeg = 57.295779513082320876798154814105

static double	Reng = 1716.56

static double	Rstar = 1545.348

static const double	SHRatio = 1.40

static const double	slugtolb = 32.174049

Detailed Description

Encapsulates various uncategorized scheduled functions.

Pilot sensed accelerations are calculated here. This is used for the coordinated turn ball instrument. Motion base platforms sometimes use the derivative of pilot sensed accelerations as the driving parameter, rather than straight accelerations.

The theory behind pilot-sensed calculations is presented:

For purposes of discussion and calculation, assume for a minute that the pilot is in space and motionless in inertial space. She will feel no accelerations. If the aircraft begins to accelerate along any axis or axes (without rotating), the pilot will sense those accelerations. If any rotational moment is applied, the pilot will sense an acceleration due to that motion in the amount:

[wdot X R] + [w X (w X R)] Term I Term II

where:

wdot = omegadot, the rotational acceleration rate vector w = omega, the rotational rate vector R = the vector from the aircraft CG to the pilot eyepoint

The sum total of these two terms plus the acceleration of the aircraft body axis gives the acceleration the pilot senses in inertial space. In the presence of a large body such as a planet, a gravity field also provides an accelerating attraction. This acceleration can be transformed from the reference frame of the planet so as to be expressed in the frame of reference of the aircraft. This gravity field accelerating attraction is felt by the pilot as a force on her tushie as she sits in her aircraft on the runway awaiting takeoff clearance.

In JSBSim the acceleration of the body frame in inertial space is given by the F = ma relation. If the vForces vector is divided by the aircraft mass, the acceleration vector is calculated. The term wdot is equivalent to the JSBSim vPQRdot vector, and the w parameter is equivalent to vPQR.

Author: Tony Peden, Jon Berndt

Version

Id: FGAuxiliary.h,v 1.31 2015/09/20 20:53:13 bcoconni Exp

Definition at line 109 of file FGAuxiliary.h.

Constructor & Destructor Documentation

◆ FGAuxiliary()

FGAuxiliary ( FGFDMExec * Executive )

Constructor.

Parameters

Executive a pointer to the parent executive object

Definition at line 62 of file FGAuxiliary.cpp.

                                          : FGModel(fdmex)
 {
   Name = "FGAuxiliary";
   pt = 1.0;
   tat = 1.0;
   tatc = RankineToCelsius(tat);
 
   vcas = veas = 0.0;
   qbar = qbarUW = qbarUV = 0.0;
   Mach = MachU = MachPitot = 0.0;
   alpha = beta = 0.0;
   adot = bdot = 0.0;
   gamma = Vt = Vground = Vpitot = 0.0;
   psigt = 0.0;
   day_of_year = 1;
   seconds_in_day = 0.0;
   hoverbmac = hoverbcg = 0.0;
   Re = 0.0;
   Nz = Ny = 0.0;
 
   vPilotAccel.InitMatrix();
   vPilotAccelN.InitMatrix();
   vAeroUVW.InitMatrix();
   vAeroPQR.InitMatrix();
   vMachUVW.InitMatrix();
   vWindUVW.InitMatrix();
   vPitotUVW.InitMatrix();
   vEuler.InitMatrix();
   vEulerRates.InitMatrix();
 
   bind();
 
   Debug(0);
 }

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Member Function Documentation

◆ GetMach()

double GetMach ( void ) const

inline

Gets the Mach number.

Definition at line 220 of file FGAuxiliary.h.

220 { return Mach; }

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◆ GetMachU()

double GetMachU ( void ) const

inline

The mach number calculated using the vehicle X axis velocity.

Definition at line 223 of file FGAuxiliary.h.

223 { return MachU; }

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◆ GetNy()

double GetNy ( void ) const

inline

The lateral acceleration in g's of the aircraft center of gravity.

Definition at line 229 of file FGAuxiliary.h.

229 { return Ny; }

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◆ GetNz()

double GetNz ( void ) const

inline

The vertical acceleration in g's of the aircraft center of gravity.

Definition at line 226 of file FGAuxiliary.h.

226 { return Nz; }

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◆ GetTb2w()

const FGMatrix33& GetTb2w ( void )

inline

Calculates and returns the body-to-wind axis transformation matrix.

Returns: a reference to the wind-to-body transformation matrix.

Definition at line 203 of file FGAuxiliary.h.

203 { return mTb2w; }

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◆ GetTotalPressure()

double GetTotalPressure ( void ) const

inline

Returns the total pressure.

Total pressure is freestream total pressure for subsonic only. For supersonic it is the 1D total pressure behind a normal shock.

Definition at line 149 of file FGAuxiliary.h.

149 { return pt; }

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◆ GetTotalTemperature()

double GetTotalTemperature ( void ) const

inline

Returns the total temperature.

The total temperature ("tat", isentropic flow) is calculated:

tat = in.Temperature*(1 + 0.2*Mach*Mach)

(where "in.Temperature" is standard temperature calculated by the atmosphere model)

Definition at line 158 of file FGAuxiliary.h.

158 { return tat; }

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◆ GetTw2b()

const FGMatrix33& GetTw2b ( void )

inline

Calculates and returns the wind-to-body axis transformation matrix.

Returns: a reference to the wind-to-body transformation matrix.

Definition at line 198 of file FGAuxiliary.h.

198 { return mTw2b; }

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◆ GetVcalibratedFPS()

double GetVcalibratedFPS ( void ) const

inline

Returns Calibrated airspeed in feet/second.

Definition at line 133 of file FGAuxiliary.h.

133 { return vcas; }

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◆ GetVcalibratedKTS()

double GetVcalibratedKTS ( void ) const

inline

Returns Calibrated airspeed in knots.

Definition at line 135 of file FGAuxiliary.h.

135 { return vcas*fpstokts; }

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◆ GetVequivalentFPS()

double GetVequivalentFPS ( void ) const

inline

Returns equivalent airspeed in feet/second.

Definition at line 137 of file FGAuxiliary.h.

137 { return veas; }

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◆ GetVequivalentKTS()

double GetVequivalentKTS ( void ) const

inline

Returns equivalent airspeed in knots.

Definition at line 139 of file FGAuxiliary.h.

139 { return veas*fpstokts; }

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◆ GetVground()

double GetVground ( void ) const

inline

Gets the ground speed in feet per second.

The magnitude is the square root of the sum of the squares (RSS) of the vehicle north and east velocity components.

Returns: The magnitude of the vehicle velocity in the horizontal plane.

Definition at line 217 of file FGAuxiliary.h.

217 { return Vground; }

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◆ GetVt()

double GetVt ( void ) const

inline

Gets the magnitude of total vehicle velocity including wind effects in feet per second.

Definition at line 211 of file FGAuxiliary.h.

211 { return Vt; }

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◆ GetVtrueFPS()

double GetVtrueFPS ( ) const

inline

Returns the true airspeed in feet per second.

Definition at line 141 of file FGAuxiliary.h.

141 { return vtrue; }

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◆ GetVtrueKTS()

double GetVtrueKTS ( ) const

inline

Returns the true airspeed in knots.

Definition at line 143 of file FGAuxiliary.h.

143 { return vtrue * fpstokts; }

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◆ Run()

bool Run ( bool Holding )

virtual

Runs the Auxiliary routines; called by the Executive Can pass in a value indicating if the executive is directing the simulation to Hold.

Parameters

Holding if true, the executive has been directed to hold the sim from advancing time. Some models may ignore this flag, such as the Input model, which may need to be active to listen on a socket for the "Resume" command to be given.

Returns: false if no error

Reimplemented from FGModel.

Definition at line 140 of file FGAuxiliary.cpp.

 {
   if (FGModel::Run(Holding)) return true; // return true if error returned from base class
   if (Holding) return false;
 
   // Rotation
 
   vEulerRates(eTht) = in.vPQR(eQ)*in.CosPhi - in.vPQR(eR)*in.SinPhi;
   if (in.CosTht != 0.0) {
     vEulerRates(ePsi) = (in.vPQR(eQ)*in.SinPhi + in.vPQR(eR)*in.CosPhi)/in.CosTht;
     vEulerRates(ePhi) = in.vPQR(eP) + vEulerRates(ePsi)*in.SinTht;
   }
 
   // Combine the wind speed with aircraft speed to obtain wind relative speed
   vAeroPQR = in.vPQR - in.TurbPQR;
   vAeroUVW = in.vUVW - in.Tl2b * in.TotalWindNED;
 
   Vt = vAeroUVW.Magnitude();
   alpha = beta = adot = bdot = 0;
   double AeroU2 = vAeroUVW(eU)*vAeroUVW(eU);
   double AeroV2 = vAeroUVW(eV)*vAeroUVW(eV);
   double AeroW2 = vAeroUVW(eW)*vAeroUVW(eW);
   double mUW = AeroU2 + AeroW2;
 
   double Vt2 = Vt*Vt;
 
   if ( Vt > 0.001 ) {
     if (vAeroUVW(eW) != 0.0)
       alpha = AeroU2 > 0.0 ? atan2(vAeroUVW(eW), vAeroUVW(eU)) : 0.0;
     if (vAeroUVW(eV) != 0.0)
       beta  =    mUW > 0.0 ? atan2(vAeroUVW(eV), sqrt(mUW)) : 0.0;
 
     //double signU=1;
     //if (vAeroUVW(eU) < 0.0) signU=-1;
 
     if ( mUW >= 0.001 ) {
       double Vtdot = (vAeroUVW(eU)*in.vUVWdot(eU) + vAeroUVW(eV)*in.vUVWdot(eV) + vAeroUVW(eW)*in.vUVWdot(eW))/Vt;
       adot = (vAeroUVW(eU)*in.vUVWdot(eW) - vAeroUVW(eW)*in.vUVWdot(eU))/mUW;
       // bdot = (signU*mUW*in.vUVWdot(eV)
       //        - vAeroUVW(eV)*(vAeroUVW(eU)*in.vUVWdot(eU) + vAeroUVW(eW)*in.vUVWdot(eW)))/(Vt2*sqrt(mUW));
       bdot = (in.vUVWdot(eV)*Vt - vAeroUVW(eV)*Vtdot)/(Vt*sqrt(mUW));
     }
   }
 
   UpdateWindMatrices();
 
   Re = Vt * in.Wingchord / in.KinematicViscosity;
 
   double densityD2 = 0.5*in.Density;
 
   qbar = densityD2 * Vt2;
   qbarUW = densityD2 * (mUW);
   qbarUV = densityD2 * (AeroU2 + AeroV2);
   Mach = Vt / in.SoundSpeed;
   MachU = vMachUVW(eU) = vAeroUVW(eU) / in.SoundSpeed;
   vMachUVW(eV) = vAeroUVW(eV) / in.SoundSpeed;
   vMachUVW(eW) = vAeroUVW(eW) / in.SoundSpeed;
 
   // Position
 
   Vground = sqrt( in.vVel(eNorth)*in.vVel(eNorth) + in.vVel(eEast)*in.vVel(eEast) );
 
   psigt = atan2(in.vVel(eEast), in.vVel(eNorth));
   if (psigt < 0.0) psigt += 2*M_PI;
   gamma = atan2(-in.vVel(eDown), Vground);
 
   tat = in.Temperature*(1 + 0.2*Mach*Mach); // Total Temperature, isentropic flow
   tatc = RankineToCelsius(tat);
 
   // Pitot
 
   vWindUVW(eU) = Vt;
   vPitotUVW = mTw2p * vWindUVW;
   Vpitot = vPitotUVW(eU);
   if (Vpitot < 0.0) Vpitot = 0.0;
   MachPitot = Vpitot / in.SoundSpeed;
   pt = PitotTotalPressure(MachPitot, in.Pressure);
 
   if (abs(MachPitot) > 0.0) {
     vcas = VcalibratedFromMach(MachPitot, in.Pressure, in.PressureSL, in.DensitySL);
     veas = sqrt(2 * qbar / in.DensitySL);
     vtrue = 1116.43559 * Mach * sqrt(in.Temperature / 518.67);
   } else {
     vcas = veas = vtrue = 0.0;
   }
 
   vPilotAccel.InitMatrix();
   vNcg = in.vBodyAccel/in.SLGravity;
   // Nz is Acceleration in "g's", along normal axis (-Z body axis)
   Nz = -vNcg(eZ);
   Ny =  vNcg(eY);
   vPilotAccel = in.vBodyAccel + in.vPQRidot * in.ToEyePt;
   vPilotAccel += in.vPQRi * (in.vPQRi * in.ToEyePt);
 
   vNwcg = mTb2w * vNcg;
   vNwcg(eZ) = 1.0 - vNwcg(eZ);
 
   vPilotAccelN = vPilotAccel / in.SLGravity;
 
   // VRP computation
   vLocationVRP = in.vLocation.LocalToLocation( in.Tb2l * in.VRPBody );
 
   // Recompute some derived values now that we know the dependent parameters values ...
   hoverbcg = in.DistanceAGL / in.Wingspan;
 
   FGColumnVector3 vMac = in.Tb2l * in.RPBody;
   hoverbmac = (in.DistanceAGL + vMac(3)) / in.Wingspan;
 
   return false;
 }

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The documentation for this class was generated from the following files:

Classes

Public Member Functions

Public Attributes

Additional Inherited Members

Detailed Description

Constructor & Destructor Documentation

◆ FGAuxiliary()

Member Function Documentation

◆ GetMach()

◆ GetMachU()

◆ GetNy()

◆ GetNz()

◆ GetTb2w()

◆ GetTotalPressure()

◆ GetTotalTemperature()

◆ GetTw2b()

◆ GetVcalibratedFPS()

◆ GetVcalibratedKTS()

◆ GetVequivalentFPS()

◆ GetVequivalentKTS()

◆ GetVground()

◆ GetVt()

◆ GetVtrueFPS()

◆ GetVtrueKTS()

◆ Run()