SS.Aerodynamics 1.2.0

export record AeroForces(public double dynamicPressure, public double lift, public double drag, public double liftToDrag)

export function airfoilPolar(string name, double[] alphaRadians, double[] liftCoefficients, double[] dragCoefficients, double[] momentCoefficients, double minimumReynolds, double maximumReynolds, double maximumMach)->AirfoilPolar

export record AirfoilPolar(public string name, public double[] alphaRadians, public double[] liftCoefficients, public double[] dragCoefficients, public double[] momentCoefficients, public double minimumReynolds, public double maximumReynolds, public double maximumMach)

export function aspectRatio(WingPlanform value)->double

export record Atmosphere(public double altitude, public double temperature, public double pressure, public double density, public double speedOfSound)

export function compressibleSubsonicCorrection(double incompressibleCoefficient, double mach, double alphaRadians, double stallAlphaLimit, double maximumMach)->CompressibleSubsonicResult

export record CompressibleSubsonicResult(public double mach, public double beta, public double correctionFactor, public double incompressibleCoefficient, public double correctedCoefficient, public double maximumMach, public double stallAlphaLimit)

export function drag(double density, double speed, double area, double dragCoefficient)->double

export function dynamicPressure(double density, double speed)->double

export function flightEnvelope(WingPlanform planform, AirfoilPolar polar, double altitude, double[] speeds, double[] alphaRadians, double dynamicViscosity, double centreOfGravityFraction)->FlightEnvelope

export record FlightEnvelope(public FlightPoint[] points, public int bestLiftToDragIndex, public double bestLiftToDrag, public double minimumLift, public double maximumLift, public double maximumDrag)

export record FlightPoint(public double altitude, public double speed, public double alphaRadians, public double mach, public double reynolds, public double liftCoefficient, public double dragCoefficient, public double momentCoefficient, public double dynamicPressure, public double lift, public double drag, public double pitchMoment, public double liftToDrag)

export function forces(double density, double speed, double area, double liftCoefficient, double dragCoefficient)->AeroForces

export function importAirfoilPolar(string source, string name, double[] alphaRadians, double[] liftCoefficients, double[] dragCoefficients, double[] momentCoefficients, double minimumReynolds, double maximumReynolds, double maximumMach)->ImportedAirfoilPolar

export record ImportedAirfoilPolar(public string source, public AirfoilPolar polar, public double minimumAlphaRadians, public double maximumAlphaRadians, public bool extrapolationPermitted)

export function inducedDragCoefficient(double liftCoefficient, double aspectRatio, double oswaldEfficiency)->double

export function interpolatePolar(AirfoilPolar polar, double alphaRadians)->PolarPoint

export function lift(double density, double speed, double area, double liftCoefficient)->double

export record LiftingLineResult(public double alphaRadians, public double liftCoefficient, public double inducedDragCoefficient, public double effectiveLiftCurveSlope, public double[] normalizedSpanStations, public double[] spanwiseLiftLoading)

export function liftingLineWing(WingPlanform planform, AirfoilPolar polar, double alphaRadians, double mach, int stationCount)->LiftingLineResult

export function loadFactorLevelTurn(double bankAngle)->double

export function longitudinalStability(AirfoilPolar polar, double alphaRadians, double mach, double centreOfGravityFraction)->LongitudinalStability

export record LongitudinalStability(public double neutralPointFraction, public double centreOfGravityFraction, public double staticMargin, public double liftCurveSlope, public double pitchMomentSlope, public bool staticallyStable)

export function machNumber(double speed, double speedOfSound)->double

export function operatingPoint(WingPlanform planform, AirfoilPolar polar, double altitude, double speed, double alphaRadians, double dynamicViscosity, double centreOfGravityFraction)->FlightPoint

export record PolarPoint(public double alphaRadians, public double liftCoefficient, public double dragCoefficient, public double momentCoefficient, public double liftCurveSlope, public double momentCurveSlope)

export function stabilityDerivativeMatrix(string[] stateNames, string[] responseNames, double[] perturbationMagnitudes, double[][] negativeResponses, double[][] positiveResponses)->StabilityDerivativeResult

export record StabilityDerivativeResult(public string[] stateNames, public string[] responseNames, public double[] derivatives, public int stateCount, public int responseCount, public string differencingMethod)

export function stallSpeed(double weight, double density, double area, double maximumLiftCoefficient)->double

export function standardAtmosphere(double altitude)->Atmosphere

export function trimOperatingPoint(WingPlanform planform, AirfoilPolar polar, double altitude, double speed, double weight, double centreOfGravityFraction, double controlMomentPerRadian, double maximumControlDeflection)->TrimResult

export record TrimResult(public bool feasible, public string reason, public double alphaRadians, public double controlDeflectionRadians, public double requiredLiftCoefficient, public double achievedLiftCoefficient, public double residualLift, public double residualMomentCoefficient)

export function wing(string name, double area, double span, double meanChord, double oswaldEfficiency)->WingPlanform

export record WingPlanform(public string name, public double area, public double span, public double meanChord, public double oswaldEfficiency)