Chaos::FAerofoil Class Reference

#include <AerofoilSystem.h>

Inheritance diagram for Chaos::FAerofoil:

Public Member Functions
	FAerofoil ()
	FAerofoil (const FAerofoilConfig *SetupIn)
void	SetAerofoilId (int Id)
void	SetControlSurface (float CtrlSurfaceInput)
void	SetDensityOfMedium (float InDensity)
FVector	GetAxis ()
FVector	GetOffset ()
FVector	GetCenterOfLiftOffset ()
FVector	GetForce (FTransform &BodyTransform, const FVector &v, float Altitude, float DeltaTime)
float	CalcDynamicPressure (float VelocitySqr, float InAltitude)
float	CalcCentreOfLift ()
float	CalcDragCoefficient (float InAngleOfAttack, float InControlSurfaceAngle)
float	CalcLiftCoefficient (float InAngleOfAttack, float InControlSurfaceAngle)
float	CalcAngleOfAttackDegrees (const FVector &UpAxis, const FVector &InAirflowVector)
Public Member Functions inherited from TVehicleSystem< FAerofoilConfig >
	TVehicleSystem ()
	TVehicleSystem (const FAerofoilConfig *SetupIn)
FAerofoilConfig &	AccessSetup ()
const FAerofoilConfig &	Setup () const

Additional Inherited Members
Public Attributes inherited from TVehicleSystem< FAerofoilConfig >
const FAerofoilConfig *	SetupPtr

Constructor & Destructor Documentation

FAerofoil() [1/2]

Chaos::FAerofoil::FAerofoil ( )

inline

FAerofoil() [2/2]

Chaos::FAerofoil::FAerofoil

(

const FAerofoilConfig *

SetupIn

)

Member Function Documentation

CalcAngleOfAttackDegrees()

float Chaos::FAerofoil::CalcAngleOfAttackDegrees	(	const FVector &	UpAxis,
		const FVector &	InAirflowVector
	)

Angle of attack is the angle between the aerofoil and the airflow vector

CalcCentreOfLift()

float Chaos::FAerofoil::CalcCentreOfLift

(

)

Center of lift moves fore/aft based on current AngleOfAttack

CalcDragCoefficient()

float Chaos::FAerofoil::CalcDragCoefficient	(	float	InAngleOfAttack,
		float	InControlSurfaceAngle
	)

Returns drag coefficient for the current angle of attack of the aerofoil surface

CalcDynamicPressure()

float Chaos::FAerofoil::CalcDynamicPressure	(	float	VelocitySqr,
		float	InAltitude
	)

Dynamic air pressure = 0.5 * AirDensity * Vsqr This function reduces the dynamic pressure in a linear fashion with altitude between MinCeiling & MaxCeiling in order to limit the aircrafts altitude with a 'natural feel' without having a hard limit

CalcLiftCoefficient()

float Chaos::FAerofoil::CalcLiftCoefficient	(	float	InAngleOfAttack,
		float	InControlSurfaceAngle
	)

Returns lift coefficient for the current angle of attack of the aerofoil surface Cheating by making control surface part of entire aerofoil movement

GetAxis()

FVector Chaos::FAerofoil::GetAxis ( )

inline

GetCenterOfLiftOffset()

FVector Chaos::FAerofoil::GetCenterOfLiftOffset

(

)

GetForce()

FVector Chaos::FAerofoil::GetForce	(	FTransform &	BodyTransform,
		const FVector &	v,
		float	Altitude,
		float	DeltaTime
	)

GetOffset()

FVector Chaos::FAerofoil::GetOffset ( )

inline

SetAerofoilId()

void Chaos::FAerofoil::SetAerofoilId ( int  Id )

inline

Set a debug Id so we can identify an individual aerofoil

SetControlSurface()

void Chaos::FAerofoil::SetControlSurface ( float  CtrlSurfaceInput )

inline

SetDensityOfMedium()

void Chaos::FAerofoil::SetDensityOfMedium ( float  InDensity )

inline

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

• Engine/Source/Runtime/Experimental/ChaosVehicles/ChaosVehiclesCore/Public/AerofoilSystem.h
• Engine/Source/Runtime/Experimental/ChaosVehicles/ChaosVehiclesCore/Private/AerofoilSystem.cpp