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Helicopter Flight Model Config (XML)
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Helicopter Flight Model Config (XML)
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=== Stabilizers === Stabilizers are simulated with ''FGHelicopterStabilizerWing'' class. It is derived from ''FGWing'' and inherits most of the functionality from it. It extends ''FGWing'' by adding downwash and dynamic pressure change effects. [[Image:RLIBDOC09.jpg|thumb|center|800px|Figure 6.8 FGHelicopterStabilizerWing model inputs and outputs]] ==== ''FGHelicopterStabilizerWing'' configuration ==== GenHeli600 allows definition of one vertical and two horizontal stabilizers. The definitions of the stabilizers are made in <VerticalStabilizer>, <HorizontalStabilizerRight> and <HorizontalStabilizerLeft> sections in the configuration file. Simplified layout of the configuration is provided below. <syntaxhighlight lang="xml"> <HorizontalStabilizerRight> <Geometry> <Position x y z /> <-- aerodynamic center of the wing with respect to the reference datum in meters --> <Up x y z /> <-- vector of the wing UP direction in vehicle body coordinates --> <Front x y z /> <-- vector of the wing FRONT direction in vehicle body coordinates --> <SurfaceArea area /> <-- m2 --> </Geometry> <AerodynamicFeatures> <DynamicPressureRatio> <AoA> AoA_1 ratio_1 AoA_2 ratio_2 . . . AoA_n ratio_n </AoA> <Sideslip> Sideslip_1 ratio_1 Sideslip_2 ratio_2 . . . Sideslip_n ratio_n </Sideslip> </DynamicPressureRatio> <MainRotorDownwash> <Low_a1 a1> WakeSkew_1 DownwashFactor1 WakeSkew_2 DownwashFactor2 . . . WakeSkew_n DownwashFactorn </Low_a1> <Medium_a1 a1> WakeSkew_1 DownwashFactor_1 WakeSkew_2 DownwashFactor_2 . . . WakeSkew_n DownwashFactor_n </Medium_a1> <High_a1 a1> WakeSkew_1 DownwashFactor_1 WakeSkew_2 DownwashFactor_2 . . . WakeSkew_n DownwashFactor_n </High_a1> </MainRotorDownwash> <MainRotorInplanewash> --> As in MainRotorDownwash <-- </MainRotorInplanewash> <LiftCurve> AoA_1 Cl_1 AoA_2 Cl_2 . . . AoA_n Cl_n </LiftCurve> <DragCurve > AoA_1 Cd_1 AoA_2 Cd_2 . . . AoA_n Cd_n </DragCurve> </AerodynamicFeatures> <HorizontalStabilizerRight> </syntaxhighlight> '''DynamicPressureRatio''' It is possible that due to interference with the fuselage, dynamic pressure observed at the stabilizers are different than the one which is computed using air density and the velocity. This effect is simulated using curves which contain the dynamic pressure ratio vs. fuselage angle of attack and side slip angles. Following equation is used: '''Stabilizer Dynamic Pressure = Dynamic Pressure * RatioAoA * RatioSideslip''' Here RatioAoA is looked up from <AoA> section (angles in degrees, ratio unitless), and RatioSideslip from <sideslip> (angles in degrees, ratio unitless) sections. '''MainRotorDownwash and MainRotorInplanewash''' Each of these sections contain three curves which define the relationship between the induced velocity acting on the stabilizer and the induced velocity of the main rotor. MainRotorDownwash is used to compute Cdownwash and MainRotorInplanewash is used to compute Cinplanewash. These are used to compute the rotorwash acting on the stabilizer as follows: '''Downwash (positive downwards) = Main Rotor Induced Velocity * Cdownwash''' '''Inplanewash (positive backwards) = Main Rotor Induced Velocity * Cinplanewash''' MainRotorDownwash and MainRotorInplanewash can contain three curves for three different a1 (main rotor longitudinal flapping in degrees) values. Depending on current a1, two nearest curves are selected and the coefficients for the current wake skew angle are looked up. Final coefficient is found by linear interpolation between the look-up values. '''LiftCurve and DragCurve''' These curves contain the coefficient of lift and drag vs. angle of attack. Coefficients are unitless and angle of attack is in degrees.
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