ACPro Module

Directory List

ACDesign

AircraftDesign	Design an aircraft for a trajectory.
AircraftDragDataStructures	Generates data structures for select aircraft.
AircraftGroupMassStatement	Create a mass statement for an aircraft.
AirlinerSeat	Generate CAD data for an airliner seat.
AirlinerSeats	Layout airliner seats.

ACEngine

AOverAStar	A/A* computation from mach number and ratio of specific heats.
AerodynamicShock	Compute Mach number and pressure for aerodynamics shocks.
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.
InletLoss	Computes the inlet loss in an aircraft engine due to shockwaves.
JetEngineAnalysis	Jet engine analysis. You can vary up to two of the
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. An
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.
PressureRatioFromTemp	Computes pressure ratio from temperature ratio, efficiency and gamma.
PressureTotal	Total pressure.
PropellerEfficiency	Computes propeller efficency from Mach number.
PropellerPower	Propeller power and induced velocity
PropellerPowerVsV	Power vs. velocity for a propeller
RFromCPAndGamma	Computes R from cP and gamma.
RamRecovery	Ram recovery in an inlet. This computes the loss of pressure due to
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 pressure.
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.

ACFlex

BldFlex

Creates the flex model interfaces.

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.
AircraftGroupDataStructure	Build the AircraftGroupMass data structure. Enter parameter pairs.
AircraftGroupMass	Create masses for an aircraft.
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.

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.

ACProAerodynamics

AeroCoefficientPointMass	Aerodynamic model with sideforce from a rudder.
AeroForceAndTorqueCombined	Compute force and torque an aircraft from M = 0 to M = inf.
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.
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, cD = cD0 + k*cL^2
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
ParasiticDragCoefficient	Parasitic drag coefficient for a set of aircraft components.
PrandtlGlauertCorrection	Computes the Prandtl Glauert Compressibility correction.
WettedArea	Aerodynamic wetted area for different structures.

ACProControl

ACPointMassControl

Point mass control of flight path angle, velocity and angle of bank.

ACProData

CityLatLonData.mat - provides data for city latitude and longitude

FlatPlate.obj - a Wavefront OBJ file for a flate plate

FlatPlateAircraft.mat - corresponding CAD model for a flate plate

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.

ACUtils

FormFactorSurfaceOfRevolution	Computes the form factor for a body of revolution.
FormFactorWing	Computes the form factor for a wing.
MachSwept	Effective Mach number with sweep.
SurfaceAreaEllipsoid	Compute the surface area of an ellipsoid.
SurfaceAreaEllipsoidRevolution	Compute the surface area of an ellipsoid of revolution.

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.
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	Turbojet jet engine model producing thrust and specific fuel consumption.

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.
STOVL	Short Takeoff Vertical Landing aircraft model.

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.

Demos/ACDesign

AirlinerDesign	Hypersonic airliner design.
GroupMassStatement	Design an aircraft.

Demos/ACEngine

F100Demo	Look at the F100 model
JetEngineAnalysisDemo	Demo JetEngineAnalysis
JetEnginePerformanceDemo	Demo JetEnginePerformance

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

Demos/ACPointMass

AircraftTrajectoryControlSim

Script to simulate aircraft trajectory control

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.

Demos/AeroPro

Gust	See the response of an F16 to a gust using a state space model.

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.

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.
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.

Demos/Atmosphere

Atmosphere

Generate plots and a latex table of atm. properties across altitude.

Demos/Wind

NOAAWindDemo

Demonstrates NOAA Wind Model for obtaining wind data and plotting it.

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 and torque for a CAD model.

Pilots

Pilot

Build a pilot model

Wind

CityCodeLatLonParser	Parse a string representation of U.S. city lat/lon data into a MATLAB
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.

SVN Revision: 42425

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