WOLFRAM SYSTEM MODELER

TurbojetPropulsion

Turbojet propulsion (model specific parameters not set)

Diagram

Wolfram Language

In[1]:=
SystemModel["Aircraft.Physical.FixedWing.Parts.Propulsions.TurbojetPropulsion"]
Out[1]:=

Information

This turbojet propulsion model extends the ConventionalPropulsion model and models the propulsion for an aircraft using turbojet engines.

Essentially, what this model does on top of the ConventionalPropulsion model, is to:

The engine model to be used for all engines in the propulsion system can be selected by choosing the value for the Engine parameter in the General tab.

Parameters (53)

weightEst

Value:

Type: Boolean

Description: true, if weight estimation method is used for masses, center of mass location and inertia tensor

bWing

Value:

Type: Length (m)

Description: Main wing span

SrefWing

Value:

Type: Area (m²)

Description: Main wing reference area

nEng

Value:

Type: Integer

Description: Number of engines

CADshapes

Value:

Type: Boolean

Description: true, if external CAD files are used for animation

T0

Value:

Type: Temperature (K)

Description: Temperature at sea-level

rho0

Value:

Type: Density (kg/m³)

Description: Air density at sea-level

p0

Value:

Type: Pressure (Pa)

Description: Static pressure at sea-level

gammaAir

Value:

Type: Real

Description: Adiabatic index for air

convProp

Value: true

Type: Boolean

Description: =true, if conventional propulsion

kSkinNac

Value:

Type: Length (m)

Description: Nacelle surface roughness height

xCMdry

Value:

Type: Length (m)

Description: Aircraft center of mass x-coordinate w.r.t. fuselage reference point (with total mass for electric aircraft and gliders, positive x-axis towards nose)

wFus

Value:

Type: Length (m)

Description: Fuselage maximum width

hFus

Value:

Type: Length (m)

Description: Fuselage maximum height

cWingRoot

Value:

Type: Length (m)

Description: Main wing root chord (where wing intersects with fuselage)

cWingTip

Value:

Type: Length (m)

Description: Main wing tip chord

tWingRoot

Value:

Type: Length (m)

Description: Main wing root thickness

tWingTip

Value:

Type: Length (m)

Description: Main wing tip thickness

xWingRootLE

Value:

Type: Length (m)

Description: Main wing root leading edge x-coordinate w.r.t. fuselage reference point (positive x-axis towards nose)

zWingRootLE

Value:

Type: Length (m)

Description: Main wing root leading edge z-coordinate w.r.t. fuselage reference point (positive z-axis towards ground)

lambdaWing

Value:

Type: Angle (rad)

Description: Main wing sweep angle at 1/4 chord

gammaWing

Value:

Type: Angle (rad)

Description: Main wing dihedral angle

iWing

Value:

Type: Angle (rad)

Description: Main wing incidence angle

TRwing

Value:

Type: Real

Description: Main wing taper ratio

tauWing

Value:

Type: Real

Description: Ratio of thickness-to-chord ratios at the main wing tip and root

xWingAC

Value:

Type: Length (m)

Description: Main wing aerodynamic center from wing leading edge at mean chord (positive x-axis towards nose)

yWingAC

Value:

Type: Length (m)

Description: Main wing aerodynamic center from fuselage centerline (y-coordinate w.r.t. fuselage centerline of mean chord)

lambdaWingLE

Value:

Type: Angle (rad)

Description: Main wing leading edge sweep angle

lambdaWingHC

Value:

Type: Angle (rad)

Description: Main wing half-chord sweep angle

bVT

Value:

Type: Length (m)

Description: Vertical tail span

lVTcm

Value:

Type: Length (m)

Description: Vertical tail arm length (from aircraft center of mass to vertical tail 1/4 chord)

engineType

Value: 2

Type: Integer

Description: Type of engine (0 = piston, 1 = turboprop, 2 = turbojet, 3 = turbofan, 4 = electric)

wingMounted

Value:

Type: Boolean

Description: true, if engines are mounted on the main wing

xEng

Value:

Type: Length (m)

Description: Fuselage mounted engine / Single engine rear end x-location from fuselage reference point (positive x-axis towards nose)

yEngInner

Value:

Type: Length (m)

Description: Inner engines y-coordinate w.r.t. fuselage centerline

yEngOuter

Value:

Type: Length (m)

Description: Outer engines y-coordinate w.r.t. fuselage centerline

zTau

Value:

Type: Length (m)

Description: Thrust line z-coordinate w.r.t. fuselage reference point for side (#2-5) engines and single engine

zTauMid

Value:

Type: Length (m)

Description: Thrust line z-coordinate w.r.t. fuselage reference point for middle (#1) engine

kappa

Value:

Type: Angle (rad)

Description: Engine thrust line angle for side (#2-5) engines and single engine

kappaMid

Value:

Type: Angle (rad)

Description: Engine thrust line angle for middle (#1) engine

rEng1

Value: if nEng == 3 then {xCMdry - lVTcm - bVT * (3 / 4), 0, zTauMid} else if nEng == 1 then {xEng, 0, zTau} else {0, 0, 0}

Type: Length[3] (m)

Description: Location of engine 1 rear end w.r.t. fuselage reference point

rEng2

Value: if (nEng == 2 or nEng == 3 or nEng == 4) and not wingMounted then {xEng, yEngInner, zTau} else if (nEng == 2 or nEng == 4) and wingMounted then {xWingRootLE - cWingRoot / 2 - tan(lambdaWingHC) * (yEngInner - wFus / 2), yEngInner, zTau + sign(yEngOuter) * tan(gammaWing) * (yEngOuter - yEngInner) / 2} else if nEng == 3 and wingMounted then {xWingRootLE - cWingRoot / 2 - tan(lambdaWingHC) * (yEngInner - wFus / 2), yEngInner, zTau} else {0, 0, 0}

Type: Length[3] (m)

Description: Location of engine 2 rear end w.r.t. fuselage reference point

rEng3

Value: if nEng == 3 and wingMounted then {xWingRootLE - cWingRoot / 2 - tan(lambdaWingHC) * (yEngInner - wFus / 2), -yEngInner, zTau} else if (nEng == 2 or nEng == 4) and wingMounted then {xWingRootLE - cWingRoot / 2 - tan(lambdaWingHC) * (yEngInner - wFus / 2), -yEngInner, zTau + sign(yEngOuter) * tan(gammaWing) * (yEngOuter - yEngInner) / 2} else if (nEng == 2 or nEng == 3 or nEng == 4) and not wingMounted then {xEng, -yEngInner, zTau} else {0, 0, 0}

Type: Length[3] (m)

Description: Location of engine 3 rear end w.r.t. fuselage reference point

rEng4

Value: if nEng == 4 and not wingMounted then {xEng, yEngOuter, zTau} else if nEng == 4 and wingMounted then {xWingRootLE - cWingRoot / 2 - tan(lambdaWingHC) * (yEngOuter - wFus / 2), yEngOuter, zTau - tan(gammaWing) * (yEngOuter - yEngInner) / 2} else {0, 0, 0}

Type: Length[3] (m)

Description: Location of engine 4 rear end w.r.t. fuselage reference point

rEng5

Value: if nEng == 4 and wingMounted then {xWingRootLE - cWingRoot / 2 - tan(lambdaWingHC) * (yEngOuter - wFus / 2), -yEngOuter, zTau - tan(gammaWing) * (yEngOuter - yEngInner) / 2} else if nEng == 4 and not wingMounted then {xEng, -yEngOuter, zTau} else {0, 0, 0}

Type: Length[3] (m)

Description: Location of engine 5 rear end w.r.t. fuselage reference point

kappaEng1

Value: if nEng == 1 then kappa else if nEng == 3 then kappaMid else 0

Type: Angle (rad)

Description: Engine thrust line angle for Engine 1

initialMfuel

Value:

Type: Mass (kg)

Description: Initial fuel mass

rhoFuel

Value: 804

Type: Density (kg/m³)

Description: Fuel density

eFuel

Value: 43000000

Type: SpecificEnergy (J/kg)

Description: Fuel energy density

tankFudgeFactor

Value: 0.9

Type: Real

Description: Fudge factor to shrink the tank size from the maximum possible tank volume

initialFuel

Value: 0.5

Type: Real

Description: Initial fuel volume as a fraction of the fuel capacity

ctrTank

Value: true

Type: Boolean

Description: true, if aircraft is fitted with center tank

wingTank

Value: true

Type: Boolean

Description: true, if aircraft is fitted with wing tanks

Inputs (1)

flightData

Type: FlightData

Description: Global flight data variables

Connectors (2)

aircraftRP

Type: Frame_b

Description: Connector to aircraft reference point

deltaThrotCmd

Type: RealInput[5]

Description: Engine throttle commands

Components (18)

flightData

Type: FlightData

Description: Global flight data variables

energyStorage

Type: TankSystem

Description: Model for energy storage

rotEng2

Type: FixedRotation

Description: Engine 2 thrust line angle (enabled if number of engines = 2 or 3 or 4)

rotEng3

Type: FixedRotation

Description: Engine 3 thrust line angle (enabled if number of engines = 2 or 3 or 4)

rotEng4

Type: FixedRotation

Description: Engine 4 thrust line angle (enabled if number of engines = 4)

rotEng5

Type: FixedRotation

Description: Engine 5 thrust line angle (enabled if number of engines = 4)

translEng1

Type: FixedTranslation

Description: Location of engine 1 rear end w.r.t. fuselage reference point

translEng2

Type: FixedTranslation

Description: Location of engine 2 rear end w.r.t. fuselage reference point

translEng3

Type: FixedTranslation

Description: Location of engine 3 rear end w.r.t. fuselage reference point

translEng4

Type: FixedTranslation

Description: Location of engine 4 rear end w.r.t. fuselage reference point

translEng5

Type: FixedTranslation

Description: Location of engine 5 rear end w.r.t. fuselage reference point

engine1

Type: TurbojetEngine

Description: Model for engine 1

engine2

Type: TurbojetEngine

Description: Turbojet engine: unparameterized

engine3

Type: TurbojetEngine

Description: Turbojet engine: unparameterized

engine4

Type: TurbojetEngine

Description: Turbojet engine: unparameterized

engine5

Type: TurbojetEngine

Description: Turbojet engine: unparameterized

sumConsumption

Type: Sum

Description: Summing of fuel / battery energy consumption

rotEng1

Type: FixedRotation

Description: Engine 1 thrust line angle