ACPro Module |
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Directory List
ACDesign
| AdvanceRatio | Compute the propeller advance ratio |
| AircraftCostCalculation | Computes aircraft cost. |
| AircraftDesign | Design an aircraft. |
| AircraftDragDataStructures | Generates data structures for select aircraft. |
| AircraftGroupMassStatement | Create a mass statement for an aircraft. |
| AircraftPowerAndThrust | Computes aircraft power and thrust for a set of trajectory segments. |
| AircraftSizing | AIRCRAFTSIZING size an aircraft. |
| AircraftThrustFromFlight | Computes the thrust required for an aircraft trajectory |
| AircraftWeights | AIRCRAFTWEIGHTS Compute weights using a simple model. |
| AirlinerSeat | Generate CAD data for an airliner seat. |
| AirlinerSeats | Layout airliner seats. |
| Boeing737 | Look up Boeing 737-800 data parameters |
| CTPropeller | Compute the propeller thrust coefficient |
| MissileMassEstimation | Computes missile weight. |
| NFromJ | Compute the rotation rate from the advance ratio |
| NFromMT | Compute the rotation rate from the tip Mach number |
| SweepAngle | SWEEPANGLE Compute sweep angle as function of Mach number. |
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ACEngine
| AOverAStar | A/A* computation from mach number and ratio of specific heats. |
| AerodynamicShock | Compute Mach number and pressure for aerodynamics shocks. |
| EngineMap | Engine performance map from a table lookup. |
| F100 | Gas Turbine 16th-order F100 linear model: Pratt and Whitney |
| FAIR | Computes the gas constants for hydrocarbon/air mixtures. This model |
| FMixedExhaustTurbofan | Function called by FZero to solve for tauTL. Only y is used by FZero. |
| IdealJetEngineEfficiency | Computes the jet engine efficiency for an ideal turbofan engine. |
| InletLoss | Computes the inlet loss in an aircraft engine due to shockwaves. |
| JetEngineAnalysis | Jet engine analysis. |
| JetEngineDefinitions | Definitions of data. If no output arguments are specified it will |
| JetEngineEfficiency | Computes the jet engine efficiency for an engine. |
| JetEnginePerformance | Jet engine performance. You can vary up to two of the parameters in p. |
| MachAcrossShock | Compute the Mach number across a shock. |
| MachFromMassFlowParameter | Mach number from mass flow parameter. You need to enter a guess for |
| MachFromPR | Computes Mach number from pressure ratio and gamma. |
| MassFlow | Computes the mass flow divided by the inlet area. The code |
| MassFlowParameter | Mass flow parameter. |
| MassFlowParameterR | Mass flow parameter with gamma, r and Mach number as inputs. |
| MassInflowSupersonic | Mass inflow for a supersonic diffuser |
| MaxShockIncidenceAngle | Compute maximum incidence angle. |
| ObliqueShockAngle | Compute the oblique shock angle from the streamline deflection angle. |
| PlotGasTurbineData | Generate plots from the Gas Turbine analysis functions. |
| PowerPropeller | Compute propeller power. |
| PressureRatioFromTemp | Computes pressure ratio from temperature ratio, efficiency and gamma. |
| PressureTotal | Total pressure. |
| PropellerEfficiency | Computes propeller efficency from Mach number. |
| PropellerMomentum | Design a propeller using actuator disk theory |
| PropellerPower | Propeller power and induced velocity |
| RamRecovery | Ram recovery in an inlet. |
| StaticPumping | Static pumping of air. |
| StreamlineShockAngle | Compute streamline deflection angle from the oblique shock angle. |
| TempRatioFromMachAndGamma | Computes the total temperature ratio from Mach number and gamma. |
| TempRatioFromPressure | Computes temperature ratio |
| TemperatureTotal | Total temperature. |
| Theta0 | Computes the dimensionless total temperature. |
| Throttle | Computes the value of the burner temperature given the throttle ratio |
| TotalPressureAndTemperature | Computes the total pressure and temperature at a Mach number. |
| TurboRamRocket | Model of a combined cycle engine with turbofan, ramjet and rocket. |
| WriteEngineData | Write engine data to a table. |
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ACFlex
| BldFlex | Creates the flex model interfaces. |
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ACPerformance
| ACWeightEstimation | Computes aircraft weight. Any parameter can be varied except type. |
| ActiveAeroSurfacesDisplay | Color the active aerodynamic surfaces. |
| AeroFormFactor | Aerodynamic form factor. |
| AircraftEquilibrium | Computes the equilibrium thrust and wing area. |
| AlphaFromQNV | Compute angle of attack. |
| AngleOfAttackMaxLD | Angle of attack for maximum L/D. |
| BankedTurn | Compute properties for a banked turn. |
| BreguetRangeEquation | Computes the Breguet range. |
| ClimbAngle | Compute climb angle |
| ComputeAlphaConstantFlightPathAngle | Computes the angle of attack for a constant flight path angle. |
| ConcordeProperties | Returns Concorde properties. |
| ConstantDynamicPressureVelocity | Computes the velocity and Mach profile for constant dynamic pressure. |
| DragUndercarriage | Computes drag coefficient increment due to the undercarriage. |
| EnergyHeight | Compute energy height contours. |
| FlightEquilibrium | Compute flight equilibrium. |
| FuelFromRange | Computes the fuel as a function of range. |
| Glide | Compute glide angle, range and velocity.. |
| LandingDistance | Computes landing distance. |
| MassCrewAndPassenger | Mass of crew and passengers. |
| RateOfClimb | Computes the rate of climb and acceleration. |
| SonicBoom | Compute the sonic boom scale factor. |
| StallVelocity | Computes takeoff velocity. |
| Takeoff | Computes the required roll distance and liftoff velocity. |
| TakeoffDistance | Computes takeoff distance. |
| TakeoffTransition | Compute the radius and length of transition. |
| TakeoffVelocity | Computes takeoff velocity. |
| TaxiingFuel | Compute taxiing fuel. |
| TurningRadius | Compute turning radius and turning rate. |
| VStall | Computes the stall velocity. |
| WingAreaToTaper | Generates the taper and trailing edge angle for a wing. |
| WingFromParameters | Generates vertices and faces for a wing based on the wing parameters. |
| WingSizingForPullUp | Sizes a wing for dynamic pull up. |
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ACPointMass
| APMLinMod | Compute a linear model for a point mass aircraft at a flight condition. |
| AircraftPointMassCLPSim | Simulate the controlled trajectory of a point mass aircraft model. |
| AircraftPointMassControl | Compute the control inputs for a point mass aircraft model. |
| AircraftPointMassDLM | Generate a discrete time-varying linear model of a point-mass aircraft. |
| AircraftPointMassRHS | Compute the state derivatives of a point mass aircraft model. |
| AircraftPointMassRHSWithSideslip | Point mass dynamic model with sideslip as an input. |
| AircraftPointMassSim | Simulate the trajectory x(t) of a point mass aircraft model given u(t) |
| RHS2DPointMass | Simulate a point mass aircraft model in 2 dimensions. |
| RHS3DPointAircraft | 3D point aircraft model with time varying mass. |
| SimpleLiftAndDrag | Lift and drag for the drag polar. |
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ACProAerodynamics
| AeroCoefficientPointMass | Aerodynamic model with sideforce from a rudder. |
| AeroForceAndTorqueCombined | Compute force and torque an aircraft from M = 0 to M = inf. |
| BladeElement | BladeElement computes the inducted velocity |
| CD0Composite | Drag coefficient for subsonic, supersonic and hypersonic flight. |
| CDCLComposite | Lift and drag coefficients for subsonic, supersonic and hypersonic flight. |
| CDCLHypersonic | Hypersonic lift and drag coefficients for a flat plate. |
| CDCLSubsonic | Subsonic lift and drag coefficients for a flat plate. |
| CDSkinFriction | Skin friction coefficient using a variety of models. |
| CDWave | Wave drag using Ackeret theory. |
| CLCDFreeMolecular | Computes the CL and CD for free molecular flow. |
| CLCMWing | Lift and moment coefficients of a thin wing. |
| CLComposite | Lift coefficient for subsonic, supersonic and hypersonic flight. |
| CPHypersonic | Hypersonic coefficient of pressure. |
| ConcordeLD | Optimal lift and drag coefficients for the Concorde. |
| DragCoeff | Computes drag coefficients for a vehicle using simple formulas. |
| DragLoss | Compute drag loss using LiftAndDragJonesSearsHaack. |
| DragPolar | Computes the drag polar |
| DragPolarFromData | Compute the drag polar from data lift and drag coefficient data. |
| FormDragCoeff | Computes form drag including wave drag. |
| GroundEffect | Ground effect factor that multiplies the induced drag. |
| InducedDragCoeff | Induced drag coefficient for all Mach numbers. |
| LDDeltaWing | Computes the lift and drag coefficients for a swept wing |
| LiftAndDrag | Computes lift and drag coefficients for a vehicle using simple formulas. |
| LiftAndDragJonesSearsHaack | Lift and drag using the R.T. Jones, Sears, and Haack model. |
| LiftCoeff | Computes the ideal lift coefficient from 0 through supersonic. |
| LiftToDragFromMach | Computes the L/D ratio from Mach number. |
| LocalAngleOfAttack | Compute the local angle of attack. |
| LowSpeedAeroData | Generates a file for sc_aero_newtonian.cc/.h |
| OptimalAngleOfAttackHypersonic | Optimal angle of attack for hypersonic flow. |
| ParasiticDragCoefficient | Parasitic drag coefficient for a set of aircraft components. |
| PrandtlGlauertCorrection | Computes the Prandtl Glauert Compressibility correction. |
| WettedArea | Aerodynamic wetted area for different structures. |
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ACProControl
| ACPointMassControl | Point mass control of flight path angle, velocity and angle of bank. |
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ACProData
| CityLatLonData.mat | provides data for city latitude and longitude |
| FlatPlate.obj | a Wavefront OBJ file for a flat plate |
| FlatPlateAircraft.mat | corresponding CAD model for a flat plate |
| Gulfstream.mat | Gulfstream aircraft model |
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ACThermal
| AerodynamicHeatFlux | Heat flux as a function of mach number. |
| DynamicPressureAndHeat | Heat, velocity and temperature at a fixed dynamic pressure. |
| StagnationPAndT | Stagnation conditions for a gas. |
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ACUtils
| FLToM | Convert flight level to meters |
| FormFactorSurfaceOfRevolution | Computes the form factor for a body of revolution. |
| FormFactorWing | Computes the form factor for a wing. |
| MachSwept | Effective Mach number with sweep. |
| SurfaceAreaEllipsoidRevolution | Compute the surface area of an ellipsoid of revolution. |
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Airbreathing
| EngineDataFromTable | Generate engine data from a table. |
| EngineExample | Example engine parameters. Returns a data structure. |
| EngineTable | Generate an engine table for a matrix of altitudes and mach. |
| HeatingValue | Heating values. |
| JetEngine | A simple jet engine model. |
| MixedFlowTurbofan | Mixed flow turbofan engine performance. |
| MixedFlowTurbofanProfile | Mixed flow turbofan engine performance profile for p, h and v. |
| Ramjet | Ramjet model including aerodynamic losses. The default fuel is H2. |
| RamjetKerrebrock | Ramjet jet engine model producing thrust and specific fuel consumption. |
| Scimitar | Models a Scimitar engine from Reaction Engines, Ltd. |
| TurboRamjet | Models a turboramjet. |
| Turbofan | Turbofan jet engine model produces thrust and specific fuel consumption. |
| Turbofanramjet | Models a turbofanramjet. |
| Turbojet | Jet engine model producing thrust and specific fuel consumption. |
| TurbojetNoThrust | Jet engine model producing zero thrust and specific fuel consumption. |
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AircraftPro
| A10 | Provides two A10 aircraft models: conventional and tilt-wing. |
| AIRC | AIRC aircraft model. |
| CCV | CCV aircraft model. |
| CCVSobel | CCV aircraft model with a pitch pointing mode. |
| CreateMVSSetupFileEntries | Creates setup file entries for MultiVehicleSim |
| F18Model | Generates a state space F-18 model from a range of models. |
| OH6A | OH6A hover model. |
| RHSRollingMissileLinear | Right-hand-side for a linear rolling missile. |
| STOVL | Short Takeoff Vertical Landing aircraft model. |
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Atmosphere
| AirMass | Computes the relative air mass to sea level and a vertical path. |
| AtmosphereLayers | Names the atmospheric layer for altitude h. |
| GeoMagLatLon | Geomagnetic latitude and longitude. |
| GeomagneticRigidity | Geomagnetic rigidity using a dipole model. |
| SonicBoomHypersonic | Hypersonic sonic boom based on drag. |
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CAD
| InletAndNozzle | Generate vertices for an inlet and a nozzle. |
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Demos/ACDesign
| AirlinerDesign | Hypersonic airliner design. |
| CostModel | Demonstrate use of the cost model |
| GroupMassStatement | Design an aircraft. |
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Demos/ACEngine
| JetEngineAnalysisDemo | Demo JetEngineAnalysis |
| JetEnginePerformanceDemo | Demo JetEnginePerformance |
| PropellerPowerVsV | Power vs. velocity for a propeller |
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Demos/ACPerformance
| BuildFlatPlateAircraft | Create a flat plate vehicle with two flaps |
| FuelConsumption | Approximate daily fuel consumption for a notional hypersonic airliner |
| RamjetConstantQ | Compute ramjet thrust for a constant dynamic pressure trajectory |
| StagnationTempDemo | Compute / plot the stagnation temperature vs. mach for several altitudes |
| TakeoffAndLanding | Compute takeoff and landing distances for a notional hypersonic airliner |
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Demos/ACPointMass
| AircraftTrajectoryControlSim | Script to simulate aircraft trajectory control |
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Demos/ACProAerodynamics
| ConcordeComparison | Compare Concorde with the CL and CD functions. |
| NewtonianAeroDemo | Compute the L/D ratio for flat surfaces in hypersonic flow. |
| SkinFrictionDemo | Skin friction and supersonic lift and drag. |
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Demos/AeroPro
| Gust | See the response of an F16 to a gust using a state space model. |
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Demos/Airbreathing
| F135Engine | Model of the Pratt & Whitney F135 Engine. |
| GenerateEngineTables | Generate ramjet and turbofan data. |
| JetFlightDemo | Aircraft takeoff demo. |
| RamjetDemo | Demonstrate a ramjet. |
| SteadyClimb | Simulate a steady climb. |
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Demos/AircraftPro
| AIRCSim | Longitudinal simulation using the AIRC aircraft model. |
| CCVEV | Demonstrate eigenvector assignment using a CCV Model |
| CCVPitchPointing | Demonstrate eigenvector assignment using an STOVL Model for transition. |
| L1011EV | Demonstrate eigenvector assignment using a CCV Model |
| L1011EVConstraints | Demonstrate eigenvector assignment using an L1011 STOVL Model. |
| LQLTR | Demonstrate linear quadratic regulator with loop transfer recovery. |
| LQOF | Demonstrate linear quadratic output feedback. |
| OH6ABryson | Run a linearized simulation of the OH6A. |
| OH6ASim | Run a linearized simulation of the OH6A. |
| RollingMissileSimulation | Rolling missile simulation |
| STOVLEV | Demonstrate eigenvector assignment using an STOVL Model |
| STOVLLatTransitionEV | Demonstrate eigenvector assignment using an STOVL Model for transition. |
| STOVLLonHoverEV | Demonstrate eigenvector assignment using an STOVL Model |
| STOVLLonTransitionEV | Demonstrate eigenvector assignment using an STOVL Model for transition. |
| STOVLTransitionEV | Demonstrate eigenvector assignment using an STOVL Model for transition. |
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Demos/Atmosphere
| Atmosphere | Generate plots and a latex table of atm. properties across altitude. |
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Demos/Trajectory
| AircraftSim | Simulate the trajectory of the aircraft |
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Demos/Wind
| NOAAWindDemo | Demonstrates NOAA Wind Model for obtaining wind data and plotting it. |
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ModelCreation
| CreateAircraftModel | Interactive tool to create an aircraft model. |
| DrawAircraft | Draws an aircraft |
| DrawAlphaBeta | Draws angle of attack and sideslip |
| DrawAngles | Draws angles and arcs between them. |
| GulfstreamSim | Simulate a Gulfstream performing a coordinated turn. |
| LiftCoeffStall | Computes the lift coefficient using a table lookup. |
| PropellerThrust | Propeller thrust |
| RHSACFlatEarth | Dynamics model for an aircraft on a flat Earth |
| RHSFlatEarthSet | Finds the set point for RHSFlatEarth with fminsearch |
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Newtonian
| NewtonianAeroTable | Generates a file for sc_aero_newtonian.cc/.h |
| NewtonianAerodynamicsFromCAD | Compute force and torque for a CAD model. |
| NewtonianAlphaFromCAD | Compute the static angle of attack to balance gravity. |
| NewtonianCPFromCAD | Compute the center of pressure from the cad model. |
| NewtonianForceFromCAD | Compute force for a CAD model. |
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Pilots
| Pilot | Build a pilot model |
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RDE
| HyperRDE | RDE model with a turbocharger. |
| RDE | RDE model producing zero thrust and specific fuel consumption. |
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Trajectory
| AircraftTrajectoryControl | AIRCRAFTPOINTMASSCONTROL Control function for a 3D point mass aircraft. |
| EquilibriumControls | EquilibriumControls finds controls to maintain equilibrium. |
| RHSPointMassAircraft | RHSPointMassAircraft Right hand side for a point mass aircraft |
| ThrustConstant | Constant thrust and fuel consumption model |
| Trajectory | Determines the set points to achieve a trajectory |
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Wind
| HorizontalWind | Horizontal wind model HWM93 covering all altitude regions |
| MergeNOAAWindData | Merge two NOAA wind data sets. There are two possibilities: |
| NOAAWindData | Load wind data from the NOAA web site. The web site is: |
| PlotWindField | Plot the wind field from a data structure array. |
| WindFunction | Approximate the Horizontal Wind Model (HWM93) with analytic functions |
| WindGust | Wind gust model. Generates state space equations or spectral densities. |
| WindModel | Combined steady-state and gust model for wind. To be used in simulation. |
| WindTrendsDemo | Animate the variation of wind magnitude and direction. |
| WindsGUI | GUI for generating wind data over a range of parameters |
| WindsPlot | Generate 3D plots of wind data vs. altitude, latitude, longitude, time. |
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