| TVehicleSystem
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Module |
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Header |
/Engine/Source/Runtime/Experimental/ChaosVehicles/ChaosVehiclesCore/Public/AerofoilSystem.h |
Include |
#include "AerofoilSystem.h" |
class FAerofoil : public TVehicleSystem< FAerofoilConfig >
Name | Description | |
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FAerofoil() |
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FAerofoil ( |
Name | Description | ||
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float |
CalcAngleOfAttackDegrees |
Angle of attack is the angle between the aerofoil and the airflow vector |
|
float |
CalcCentreOfLift() |
Center of lift moves fore/aft based on current AngleOfAttack |
|
float |
CalcDragCoefficient ( |
Returns drag coefficient for the current angle of attack of the aerofoil surface |
|
float |
CalcDynamicPressure ( |
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 |
|
float |
CalcLiftCoefficient ( |
Returns lift coefficient for the current angle of attack of the aerofoil surface Cheating by making control surface part of entire aerofoil movement |
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GetAxis() |
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GetCenterOfLiftOffset() |
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GetForce ( |
Returns the combined force of lift and drag at an aerofoil in world coordinates for direct application to the aircrafts rigid body. |
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GetOffset() |
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SetAerofoilId ( |
Set a debug Id so we can identify an individual aerofoil |
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SetControlSurface ( |
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SetDensityOfMedium ( |