WOLFRAM SYSTEM MODELER

Cessna172

Model of a general aviation aircraft

Diagram

Wolfram Language

In[1]:=
SystemModel["Aircraft.Physical.FixedWing.Cessna172"]
Out[1]:=

Information

This model extends the AircraftBase model and contains the parameters of the Cessna 172 general aviation aircraft. 

References

[1] Cel, M. (2019). Cessna 172 Flight Simulation Data. 10.13140/RG.2.2.27040.51205. 

Parameters (145)

mDry

Value: 1060

Type: Mass (kg)

Description: Aircraft dry mass (total mass for electric aircraft and gliders)

initialMfuel

Value: 146.28

Type: Mass (kg)

Description: Initial fuel mass

xCMdry

Value: 1.6

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 toward nose)

yCMdry

Value: 0

Type: Length (m)

Description: Aircraft center of mass y coordinate w.r.t. fuselage reference point (with total mass for electric aircraft and gliders, positive y axis toward right)

zCMdry

Value: 0

Type: Length (m)

Description: Aircraft center of mass z coordinate w.r.t. fuselage reference point (with total mass for electric aircraft and gliders, positive z axis toward ground)

IxxDry

Value: 2424.2

Type: MomentOfInertia (kg⋅m²)

Description: Aircraft dry moment of inertia about x axis

IyyDry

Value: 2427.3

Type: MomentOfInertia (kg⋅m²)

Description: Aircraft dry moment of inertia about y axis

IzzDry

Value: 4372.5

Type: MomentOfInertia (kg⋅m²)

Description: Aircraft dry moment of inertia about z axis

IxyDry

Value: 0

Type: MomentOfInertia (kg⋅m²)

Description: Aircraft xy product of dry moment of inertia

IxzDry

Value: -161.15

Type: MomentOfInertia (kg⋅m²)

Description: Aircraft xz product of dry moment of inertia

IyzDry

Value: 0

Type: MomentOfInertia (kg⋅m²)

Description: Aircraft yz product of dry moment of inertia

MTOMdes

Value: 1200

Type: Mass (kg)

Description: Design maximum takeoff mass

nPax

Value: 3

Type: Integer

Description: Design number of passengers

mPLdes

Value: 20

Type: Mass (kg)

Description: Design payload mass

machDes

Value: 0.3

Type: Real

Description: Design Mach number

compMat

Value: false

Type: Boolean

Description: true, if composite materials are used in structures

qMax

Value: 1261700000

Type: Pressure (Pa)

Description: Maximum dynamic pressure

nMax

Value: 3

Type: Real

Description: Maximum load factor

nEng

Value: 1

Type: Integer

Description: Number of engines

wingMounted

Value: false

Type: Boolean

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

engineType

Value: 0

Type: Integer

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

bWing

Value: 11.17

Type: Length (m)

Description: Main wing span

cWingRoot

Value: 1.89

Type: Length (m)

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

cWingTip

Value: 1.34

Type: Length (m)

Description: Main wing tip chord

tWingRoot

Value: 0.21

Type: Length (m)

Description: Main wing root thickness

tWingTip

Value: 0.21

Type: Length (m)

Description: Main wing tip thickness

xWingRootLE

Value: 1.97

Type: Length (m)

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

zWingRootLE

Value: -0.65

Type: Length (m)

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

lambdaWing

Value: 0

Type: Angle (rad)

Description: Main wing sweep angle at 1/4 chord

gammaWing

Value: 0

Type: Angle (rad)

Description: Main wing dihedral angle

iWing

Value: 0

Type: Angle (rad)

Description: Main wing incidence angle

bHT

Value: 3.28

Type: Length (m)

Description: Horizontal tail span

cHTroot

Value: 1.2

Type: Length (m)

Description: Horizontal tail root chord

cHTtip

Value: 0.7

Type: Length (m)

Description: Horizontal tail tip chord

tHTroot

Value: 0.11

Type: Length (m)

Description: Horizontal tail root thickness

tHTtip

Value: 0.11

Type: Length (m)

Description: Horizontal tail tip thickness

xHTrootLE

Value: -2.49

Type: Length (m)

Description: Horizontal tail root leading edge x coordinate w.r.t. fuselage reference point (positive x axis toward nose)

zHTrootLE

Value: -0.21

Type: Length (m)

Description: Horizontal tail root leading edge z coordinate w.r.t. fuselage reference point (positive z axis toward ground)

lambdaHT

Value: 0.349065850398866

Type: Angle (rad)

Description: Horizontal tail sweep angle at 1/4 chord

iHT

Value: 0

Type: Angle (rad)

Description: Horizontal tail incidence angle

bVT

Value: 1.06

Type: Length (m)

Description: Vertical tail span

cVTroot

Value: 1.04

Type: Length (m)

Description: Vertical tail root chord

cVTtip

Value: 0.67

Type: Length (m)

Description: Vertical tail tip chord

tVTroot

Value: 0.07

Type: Length (m)

Description: Vertical tail root thickness

tVTtip

Value: 0.07

Type: Length (m)

Description: Vertical tail tip thickness

xVTrootLE

Value: -2.52

Type: Length (m)

Description: Vertical tail root leading edge x coordinate w.r.t. fuselage reference point (positive x axis toward nose)

zVTroot

Value: -0.26

Type: Length (m)

Description: Vertical tail root z coordinate w.r.t fuselage reference point

lambdaVT

Value: 1.22173047639603

Type: Angle (rad)

Description: Vertical tail sweep angle at 1/4 chord

lFus

Value: 7.56

Type: Length (m)

Description: Fuselage length

wFus

Value: 1.20

Type: Length (m)

Description: Fuselage maximum width

hFus

Value: 1.33

Type: Length (m)

Description: Fuselage maximum height

dFusHT

Value: 0.3

Type: Length (m)

Description: Fuselage diameter at horizontal tail 1/4 chord

kSkinAC

Value: 6.35e-06

Type: Length (m)

Description: Surface roughness height (same value to be used for all components)

kSkinWing

Value: kSkinAC

Type: Length (m)

Description: Main wing surface roughness height

ClAlphaWing2D

Value: 6.21

Type: CurveSlope (rad⁻¹)

Description: Change in the section lift coefficient of the main wing airfoil (2D) due to alpha

alpha0Wing2D

Value: -0.0349065850398866

Type: Angle (rad)

Description: Zero-lift angle of attack of the main wing airfoil (2D)

ClMaxWing2D

Value: 1.17

Type: Real

Description: Maximum section lift coefficient of the main wing airfoil (2D)

kSkinHT

Value: kSkinAC

Type: Length (m)

Description: Horizontal tail surface roughness height

ClAlphaHT2D

Value: 2 * Modelica.Constants.pi

Type: CurveSlope (rad⁻¹)

Description: Change in the section lift coefficient of the horizontal tail airfoil (2D) due to alpha

alpha0HT2D

Value: 0

Type: Angle (rad)

Description: Zero-lift angle of attack of the horizontal tail airfoil (2D)

ClMaxHT2D

Value: 1.2

Type: Real

Description: Maximum section lift coefficient of the horizontal tail airfoil (2D)

kSkinVT

Value: kSkinAC

Type: Length (m)

Description: Vertical tail surface roughness height

ClAlphaVT2D

Value: 2 * Modelica.Constants.pi

Type: CurveSlope (rad⁻¹)

Description: Change in the section lift coefficient of the vertical tail airfoil (2D) due to alpha

kSkinFus

Value: kSkinAC

Type: Length (m)

Description: Fuselage surface roughness height

deltaElvMax

Value: 0.488692190558412

Type: Angle (rad)

Description: Maximum elevator deflection

deltaAilMax

Value: 0.296705972839036

Type: Angle (rad)

Description: Maximum aileron deflection

deltaRdrMax

Value: 0.785398163397448

Type: Angle (rad)

Description: Maximum rudder deflection

cAil

Value: 0.125 * cWingMean

Type: Length (m)

Description: Aileron average chord

yAilRoot

Value: 2.10

Type: Length (m)

Description: Aileron root y-coordinate w.r.t. fuselage centerline

yAilTip

Value: 5.41

Type: Length (m)

Description: Aileron tip y-coordinate w.r.t. fuselage centerline

Selv

Value: 1.35

Type: Area (m²)

Description: Elevator area

Srdr

Value: 0.42

Type: Area (m²)

Description: Rudder area

sigmaBeta

Value: max(3.06 * (SrefVT / SrefWing) / (1 + cos(lambdaWing)) + 0.4 * (-tan(gammaWing) * (yWingAC - wFus / 2) + zWingRootLE) / wFus + 0.009 * (bWing ^ 2 / SrefWing) - 0.276, 0)

Type: Real

Description: Change in sidewash due to beta

rACcm

Value: if weightEst then {xWingRootLE - lambdaWingLE * (yWingAC - wFus / 2) - 0.15 * cWingMean, 0, 0} else {xCMdry, yCMdry, zCMdry}

Type: Length[3] (m)

Description: Aircraft dry center of mass w.r.t. fuselage reference point (estimated to be at 15% of MAC if weight estimation method is used)

Cfus

Value: Modelica.Constants.pi * (3 * (hFus / 2 + wFus / 2) - sqrt(10 * hFus / 2 * wFus / 2 + 3 * ((hFus / 2) ^ 2 + (wFus / 2) ^ 2)))

Type: Length (m)

Description: Fuselage circumference

SwetFus

Value: Cfus * lFus * (1 - 2 / (lFus / (Cfus / Modelica.Constants.pi))) ^ (2 / 3) * (1 + 1 / (lFus / (Cfus / Modelica.Constants.pi)) ^ 2)

Type: Area (m²)

Description: Fuselage wetted area

FFfus

Value: 1 + 0.0025 * (lFus / hFus) + 60 * (hFus / lFus) ^ 3

Type: Real

Description: Fuselage form factor

CDmaxFus

Value: 0.8 * lFus * hFus / SrefWing

Type: Real

Description: Maximum drag coefficient of the fuselage

nSeatAbs

Value: if nPax > 180 then floor(0.9 * wFus / 0.5588) - 1 else floor(0.9 * wFus / 0.5588)

Type: Real

Description: Number of seats abreast

cWingMean

Value: 1.49

Type: Length (m)

Description: Main wing mean chord length

xWingAC

Value: -0.25 * cWingMean

Type: Length (m)

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

yWingAC

Value: bWing / 6 * (cWingRoot + 2 * cWingTip) / (cWingRoot + cWingTip)

Type: Length (m)

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

SwetWing

Value: 2 * (SrefWing / cos(gammaWing) - cWingRoot * wFus) * (1 + 0.25 * (tWingRoot / cWingRoot) * (1 + tWingTip / cWingTip / (tWingRoot / cWingRoot) * TRwing) / (1 + TRwing))

Type: Area (m²)

Description: Main wing wetted area

CLmaxWing3D

Value: 0.9 * ClMaxWing2D * cos(lambdaWing)

Type: Real

Description: Maximum lift coefficient of the main wing (3D)

CDmaxWing3D

Value: 1.98 - 0.81 * (1 - Modelica.Constants.e ^ (-20 / ARwing))

Type: Real

Description: Maximum drag coefficient of the main wing (3D)

FFwing

Value: 0.421 * (2 + 4 * tWingMean / cWingMean + 240 * (tWingMean / cWingMean) ^ 4)

Type: Real

Description: Main wing form factor

sdWing

Value: 0.9998 + 0.0421 * (wFus / bWing) - 2.6286 * (wFus / bWing) ^ 2 + 2 * (wFus / bWing) ^ 3

Type: Real

Description: Fuselage drag factor for main wing

kdWing

Value: -3.333 * 10 ^ (-4) * lambdaWing ^ 2 + 6.667 * 10 ^ (-5) * lambdaWing + 0.38

Type: Real

Description: Empirical constant for Oswald efficiency factor for main wing

kCnDeltaAil

Value: -0.350894 - 0.066355 * (yAilRoot / (bWing / 2)) ^ 4.15179 + 0.029308 * (bWing ^ 2 / SrefWing)

Type: Real

Description: Empirical factor for the yaw moment derivative due to ailerons

tauAil

Value: 1.129 * (Sail / SrefWing) ^ 0.4044 - 0.1772

Type: Real

Description: Aileron effectiveness coefficient

SrefHT

Value: 2

Type: Area (m²)

Description: Horizontal tail reference area

cHTmean

Value: 2 / 3 * cHTroot * (1 + TRht + TRht ^ 2) / (1 + TRht)

Type: Length (m)

Description: Horizontal tail mean chord

SwetHT

Value: 2 * (SrefHT - cHTroot * dFusHT) * (1 + 0.25 * (tHTroot / cHTroot) * (1 + tHTtip / cHTtip / (tHTroot / cHTroot) * TRht) / (1 + TRht))

Type: Area (m²)

Description: Horizontal tail wetted area

CLmaxHT3D

Value: 0.9 * ClMaxHT2D * cos(lambdaHT)

Type: Real

Description: Maximum lift coefficient of the horizontal tail (3D)

CDmaxHT3D

Value: 1.98 - 0.81 * (1 - Modelica.Constants.e ^ (-20 / ARht))

Type: Real

Description: Maximum drag coefficient of the horizontal tail (3D)*(SrefHT/SrefWing)

FFht

Value: 1 + 0.1 * (1 - 0.893 * abs(zHTrootLE / hFus)) * (2 + 4 * tHTmean / cHTmean + 240 * (tHTmean / cHTmean) ^ 4)

Type: Real

Description: Horizontal tail form factor

sdHT

Value: 0.9998 + 0.0421 * (dFusHT / bHT) - 2.6286 * (dFusHT / bHT) ^ 2 + 2 * (dFusHT / bHT) ^ 3

Type: Real

Description: Fuselage drag factor for horizontal tail

kdHT

Value: -3.333 * 10 ^ (-4) * lambdaHT ^ 2 + 6.667 * 10 ^ (-5) * lambdaHT + 0.38

Type: Real

Description: Empirical constant for Oswald efficiency factor for horizontal tail

tauElv

Value: 1.129 * (Selv / SrefHT) ^ 0.4044 - 0.1772

Type: Real

Description: Elevator effectiveness coefficient

cVTmean

Value: 2 / 3 * cVTroot * (1 + TRvt + TRvt ^ 2) / (1 + TRvt)

Type: Length (m)

Description: Vertical tail mean chord

SwetVT

Value: 2 * SrefVT * (1 + 0.25 * (tVTroot / cVTroot) * (1 + tVTtip / cVTtip / (tVTroot / cVTroot) * TRvt) / (1 + TRvt))

Type: Area (m²)

Description: Vertical tail wetted area

FFvt

Value: 0.5 * (2 + 4 * tVTmean / cVTmean + 240 * (tVTmean / cVTmean) ^ 4)

Type: Real

Description: Vertical tail form factor

sdVT

Value: 0.9998

Type: Real

Description: Fuselage drag factor for vertical tail

kdVT

Value: -3.333 * 10 ^ (-4) * lambdaVT ^ 2 + 6.667 * 10 ^ (-5) * lambdaVT + 0.38

Type: Real

Description: Empirical constant for Oswald efficiency factor for vertical tail

tauRdr

Value: 1.129 * (Srdr / SrefVT) ^ 0.4044 - 0.1772

Type: Real

Description: Rudder effectiveness coefficient

initialAltitude

Value:

Type: Altitude (m)

Description: Initial altitude

initialLatPosition

Value: {0, 0}

Type: Position[2] (m)

Description: Initial lateral position of the aircraft (x and y coordinates in world frame)

initialVelocity

Value:

Type: Velocity (m/s)

Description: Initial velocity

initialTrack

Value: 0

Type: Angle (rad)

Description: Initial track angle

initialGamma

Value: 0

Type: Angle (rad)

Description: Initial flight path angle

initialPhi

Value: 0

Type: Angle (rad)

Description: Initial roll angle

initialTheta

Value: 0

Type: Angle (rad)

Description: Initial pitch angle

initialPsi

Value: 0

Type: Angle (rad)

Description: Initial yaw angle (heading)

initialAngularVelocity

Value: {0, 0, 0}

Type: AngularVelocity[3] (rad/s)

Description: Initial {roll [p], pitch [q], yaw [r]}

CADshapes

Value: false

Type: Boolean

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

CADpath

Value: "modelica://Aircraft/Resources/CAD/PathName.obj"

Type: String

Description: Path for CAD file

SrefWing

Value: 16.17

Type: Area (m²)

Description: Main wing reference area

SrefVT

Value: 1.71

Type: Area (m²)

Description: Vertical tail reference area

weightEst

Value: false

Type: Boolean

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

ARwing

Value: bWing ^ 2 / SrefWing

Type: Real

Description: Main wing aspect ratio

TRwing

Value: cWingTip / cWingRoot

Type: Real

Description: Main wing taper ratio

tWingMean

Value: (yWingAC - wFus / 2) * (tWingTip - tWingRoot) / (bWing / 2 - wFus / 2) + tWingRoot

Type: Length (m)

Description: Main wing mean thickness

lambdaWingLE

Value: atan((cWingRoot / 4 - cWingTip / 4 + tan(lambdaWing) * bWing / 2) / (bWing / 2))

Type: Angle (rad)

Description: Main wing leading edge sweep angle

lambdaWingHC

Value: atan((cWingTip / 4 - cWingRoot / 4 + tan(lambdaWing) * bWing / 2) / (bWing / 2))

Type: Angle (rad)

Description: Main wing half-chord sweep angle

lambdaWingTE

Value: atan((lambdaWingLE * ((bWing - wFus) / 2) + cWingTip - cWingRoot) / ((bWing - wFus) / 2))

Type: Angle (rad)

Description: Main wing trailing edge sweep angle (at ailerons location)

ARht

Value: bHT ^ 2 / SrefHT

Type: Real

Description: Aspect ratio of horizontal tail

TRht

Value: cHTtip / cHTroot

Type: Real

Description: Taper ratio of horizontal tail

tHTmean

Value: bHT / 2 * (1 + 2 * TRht) / (3 + 3 * TRht) * (tHTtip - tHTroot) / (bHT / 2 - dFusHT / 2) + tHTroot

Type: Length (m)

Description: Horizontal tail mean thickness

lHTcm

Value: abs(xHTrootLE - xCMdry - tan(lambdaHTle) * (bHT / 2 - dFusHT / 2) * (1 + 2 * TRht) / (3 + 3 * TRht) - 0.25 * cHTmean)

Type: Length (m)

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

lHTwingAC

Value: abs(xHTrootLE - (xWingRootLE - lambdaWingLE * (yWingAC - wFus / 2))) + tan(lambdaHTle) * (bHT / 2 - dFusHT / 2) * (1 + 2 * TRht) / (3 + 3 * TRht) + 0.25 * cHTmean - abs(xWingAC)

Type: Length (m)

Description: Horizontal tail arm length (from wing aerodynamic center to horizontal tail 1/4 chord)

vHT

Value: SrefHT / SrefWing * (lHTcm / cWingMean)

Type: Real

Description: Horizontal tail volume coefficient

lambdaHTle

Value: atan((cHTroot / 4 - cHTtip / 4 + tan(lambdaHT) * bHT / 2) / (bHT / 2))

Type: Angle (rad)

Description: Horizontal tail leading edge sweep angle

ARvt

Value: bVT ^ 2 / SrefVT

Type: Real

Description: Aspect ratio of vertical tail

TRvt

Value: cVTtip / cVTroot

Type: Real

Description: Taper ratio of vertical tail

tVTmean

Value: bVT * (1 + 2 * TRvt) / (3 + 3 * TRvt) * (tVTtip - tVTroot) / bVT + tVTroot

Type: Length (m)

Description: Vertical tail mean thickness

lVTcm

Value: abs(xVTrootLE - xCMdry - tan(lambdaVTle) * bVT * (1 + 2 * TRvt) / (3 + 3 * TRvt) - 0.25 * cVTmean)

Type: Length (m)

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

lVTwingAC

Value: abs(xVTrootLE - (xWingRootLE - lambdaWingLE * (yWingAC - wFus / 2))) + tan(lambdaVTle) * bVT * (1 + 2 * TRvt) / (3 + 3 * TRvt) + 0.25 * cVTmean - abs(xWingAC)

Type: Length (m)

Description: Vertical tail arm length (from wing aerodynamic center to vertical tail aerodynamic center)

zVTac

Value: zVTroot - bVT * (1 + 2 * TRvt) / (3 + 3 * TRvt)

Type: Length (m)

Description: Vertical tail center of pressure z-coordinate w.r.t. fuselage reference point

vVT

Value: SrefVT / SrefWing * (lVTcm / bWing)

Type: Real

Description: Vertical tail volume coefficient

lambdaVTle

Value: atan((tan(lambdaVT) * bVT - cVTtip / 4 + cVTroot / 4) / bVT)

Type: Angle (rad)

Description: Vertical tail leading edge sweep angle

T0

Value: atmos.T0

Type: Temperature (K)

Description: Temperature at sea level

rho0

Value: atmos.mAir * p0 / (atmos.R0 * T0)

Type: Density (kg/m³)

Description: Air density at sea level

a0

Value: sqrt(atmos.gammaAir * atmos.R0 / atmos.mAir * T0)

Type: Velocity (m/s)

Description: Speed of sound at sea level

gammaAir

Value: atmos.gammaAir

Type: Real

Description: Adiabatic index for air

tauWing

Value: tWingTip / cWingTip / (tWingRoot / cWingRoot)

Type: Real

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

Outputs (1)

xEtot

Type: Real

Description: State of aircraft total energy

Connectors (6)

deltaAilCmd

Type: RealInput

Description: Ailerons deflection command

deltaElvCmd

Type: RealInput

Description: Elevator deflection command

deltaRdrCmd

Type: RealInput

Description: Rudder deflection command

aircraftRP

Type: Frame_b

Description: Connector to aircraft reference point

flightDataOut

Type: FlightDataOut

Description: Flight data output

deltaThrotCmd

Type: RealInput[nEng]

Description: Engine throttle commands when custom propulsion is used

Components (5)

atmos

Type: AtmosphericProperties

Description: Property parameters for the U.S. Standard Atmosphere

flightData

Type: FlightData

Description: Global flight data variables (measured at the aircraft center of mass location)

body

Type: Body

Description: Model for the mass properties of entire aircraft or only fuselage, landing gear and payload if weight estimation method is used

propulsion

Type: PistonPropulsion

Description: Propulsion model

controlSurfaces

Type: Conventional

Description: Model of system of surfaces in conventional wing configuration