使用方法英文

1

*

*File:

*

*Purpo:ThisisaninputfilefortheDigitalDatcomprogram.

*

*Author:BillGalbraith

*HolyCows,Inc.

*billg(at)

*

*Lastupdate:

*May12,2010-Fixedverticalfin,removedgroundandpowereffects.

*

************************

*ListofCommandCard

************************

*

*Note:yappearin

*anyorder,withtheexceptionofNEXTCASE.

*

*NAMELISTThecontentsofeachapplicatblenamelistisdumpedforthe

*caintheinputsystemofunits.(Veryufultoe

*inputparametervalues).

*SAVEPrervetheinputdataforthecatobeudinthefollowing

*uldbeufulifmultipleorcomparisoncas

*arebuilt.

*sareFT,IN,M,CM

*NEXTCASETerminatesthereadingofinputcardsandbeginxecutionof

*taaredestroyedfollowingexecutionofaca,

*unlesstheSAVEcardisprent.

*TRIMTrimcalculationswillbeperformedforeachsubsonicMachnumber

*lemaybetrimmedbydeflectingacontrol

*deviceonthewingorhorizontaltailorbydeflectingan

*all-moveablehorizontalstabilizer.

*DAMPProvidesdynamic-derivativeresultsinadditiontothestandard

*static-derivativeoutput

*CASEIDProvidesacaidentificationthatisprintedaspartofthe

*outputheader.

*DUMPALLPrintsthecontentsofthenamedarraysinthefoot-pound-cond

*endixCforlistofarraysandtheircontents.

*DUMPCASEwillprintallthearraysthatareudduringca

*executionpriortotheconventionaloutput.(Notparticularily

*uful,asalldataisinnastyarrays)

*DUMPINPTwillprintdumpofallinputdatablocksudfortheca.

2

*(alsonotuful)

*DUMPIOMwillprintalltheoutputarraysfortheca.(notuful)

*DUMPALLwillprintallprogramarrays,evenifnotudfortheca.

*(surprisingly,notuful)

*DERIVDEGDefinestheoutputunitsofmeasureforthestaticanddynamic

*stabilityderivatives,lowingparameters

*areaffected:CLa,Cma,Cyb,Cnb,Clb,CLq,Cmq,Clp,Cyp,Cnp,

*Cnr,Clr,CLad,XMLoutputisalsoswitchedbetween

*degreesandradiansforalpha,beta,etc.

*PARTProvidesauxiliaryandpartialoutputsateachMachnumberinthe

*utputsareautomaticallyprovidedforallcasat

*transonicMachnumbers.

*tional

*staticanddynamicstabilitydataareoutputforaLOTofitems.

*PLOTCausdatageneratedbytheprogramtobewrittentological

*unit13,whichcanberetainedforinputtothePlotModule.

*(

*toouful).

DIMFT

DERIVDEG

DAMP

PART

*DUMPIOM

**********************

*FlightConditions*

**********************

*WTVehicleWeight

*LOOPProgramLoopingControl

*1=varyaltitudeandmachtogether,default)

*2=varyMach,atfixedaltitude

*3=varyaltitude,atfixedMach

*NMACHNumberofMachnumbersorvelocitiestoberun,maxof20

*Note:Thisparameter,alongwithNALT,mayaffectthe

*properttingoftheLOOPcontrolparameter.

*MACHArray(20)ValuesoffreestreamMachnumber

*VINFArray(20)Valuesoffreestreamspeed(unit:l/t)

*NALPHANumberofanglesofattacktoberun,maxof20

*ALSCHDArray(20)Valuesofanglesofattack,inascendingorder

*RNNUBArray(20)Reynoldsnumberperunitlength

*rayelementmust

3

*correspondtotherespectiveMachnumber/freestream

*speedinput,uLOOP=1.0

*NALTNumberofatmosphericconditionstoberun,maxof20

*inputaitheraltitudeorpressureandtemperature

*Note:Thisparameter,alongwithNMACH,mayaffectthe

*properttingoftheLOOPcontrolparameter.

*ALTArray(20)Valuesofgeometricaltitude

*,Atmosphericconditions

*areinputeitherasaltitudeorpressureandtemperature.(MAX20)

*PINFArray(20)ValuesoffreestreamStaticPressure

*TINFArray(20)ValuesoffreestreamTemperature

*HYPERS=.onicanalysisatallMachnumbers>1.4

*STMACHUpperlimitofMachnumbersforsubsonicanalysis

*(0.6

*TSMACHLowerlimitofMachnumberforSupersonicanalysis

*(1.01<=TSMACH<=1.4)Defaultto1.4

*TRDragduetolifttransitionflag,forregressionanalysis

*ofwing-bodyconfiguration.

*=0.0fornotransition(default)

*=1.0fortransitionstripsorfullscaleflight

*GAMMAFlightpathangle

$FLTCONWT=7000.0,LOOP=2.0,

NMACH=1.0,MACH(1)=0.4,

NALT=1.0,ALT(1)=0.0,

NALPHA=20.0,

ALSCHD(1)=-16.0,-8.0,-6.0,-4.0,-2.0,0.0,2.0,4.0,8.0,9.0,

10.0,12.0,14.0,16.0,18.0,19.0,20.0,21.0,22.0,24.0,

STMACH=0.6,TSMACH=1.4,TR=1.0$

*************************

*ReferenceParameters*pg29

*************************

*SREFReferenceareavalueoftheoreticalwingareaudbyprogram

*ifnotinput

*CBARRLongitudinalreferencelengthvalueoftheoritcalwing

*MeanAerodynamicChordudbyprogramifnotinput

*BLREFLateralreferencelengthvalueofwingspanudbyprogram

*ROUGFCSurfaceroughnessfactor,equivalentsandroughness,default

*to0.16e-3inches(Naturalsheetmetal)

*0.02/0.08E-3-Polishedmetalorwood

*0.16E-3-Naturalsheetmetal

4

*0.25E-3-Smoothmattepaint,carefullyapplied

*0.40E-3-Standardcamouflagepaint,averageapplication

$OPTINSSREF=320.8,CBARR=6.75,BLREF=51.7,ROUGFC=0.25E-3$

**************************************

*GroupIISynthesisParameters*pg33

**************************************

*

*page33

*

*XCGLongitudinallocationofcg()

*ZCGVerticallocationofCGrelativetoreferenceplane

*XWLongitudinallocationoftheoreticalwingapex(where

*leadingedgewouldinterctlongaxis)

*ZWVerticallocationoftheoreticalwingapexrelativeto

*referenceplane

*ALIWWingrootchordincidentanglemeasuredfromreferenceplane

*XHLongitudinallocationoftheoreticalhorizontaltailapex.

*IfHINAXisinput,XHandZHareevaluatedatzeroincidence.

*ZHVerticallocationoftheoreticalhorizontaltailapex

*Xisinput,XHandZH

*areevaluatedatzeroincidence.

*ALIHHorizontaltailrootchordincidenceanglemeasuredfrom

*referenceplane

*XVLongitudinallocationoftheoreticalverticaltailapex

*XVFLongitudinallocationoftheoreticalventralfinapex

*ZVVerticallocationoftheoreticalverticaltailapex

*Thiskindamakesnonlyfortwintailsthatarecanted

*ZVFVerticallocationoftheoreticalventralfinapex

*Thiskindamakesnonlyfortwintailsthatarecanted

*SCALEVehiclescalefactor(multipliertoinputdimensions)

*VERTUPVerticalpanelabovereferenceplane(default=true)

*HINAXLongitudinallocationofhorizontaltailhingeaxis.

*Requiredonlyforall-moveablehorizontaltailtrimoption.

$SYNTHSXCG=21.9,ZCG=3.125,

XW=19.1,ZW=3.125,ALIW=2.5,

XH=39.2,ZH=7.75,ALIH=0.0,

XV=36.0,ZV=6.0,

XVF=28.0,ZVF=7.4,

SCALE=1.0,VERTUP=.TRUE.$

5

**********************************

*BodyConfigurationParameters*pg36

**********************************

*HereisanerrormessageoutputbyDIGDATconcerningbodygeometry:

*INNAMELISTBODY,ONLYTHEFOLLOWINGCOMBINATIONSOFVARIABLES

CANBEUSED

*FORACIRCULARBODY,SPECIFYXANDRORXANDS

*FORANELLIPTICALBODY,SPECIFYXANDRORXANDS,ANDTHEVARIABLE

ELLIP

*FOROTHERBODYSHAPESX,R,S,ANDPMUSTALLBESPECIFIED

*

*NXNumberoflongitudinalbodystationsatwhichdatais

*specified,maxof20

*XArray(20)Longitudinaldistancemeasuredfromarbitraylocation

*SArray(20)eabove.

*PArray(20)eabove.

*RArray(20)eabove.

*ZUArray(20)Z-coordinateatupperbodysurfaceatstationXi

*(positivewhenabovecenterline)

*[Onlyrequiredforsubsonicasymmetricbodies]

*ZLArray(20)Z-coordinateatlowerbodysurfaceatstationXi

*(negativewhenbelowcenterline)

*[Onlyrequiredforsubsonicasymmetricbodies]

*BNOSENoconetype1.0=conical(rounded),2.0=ogive(sharppoint)

*[Notrequiredinsubsonicspeedregime]

*BTAILTailconetype1.0=conical,2.0=ogive,omitforlbt=0

*[Notrequiredinsubsonicspeedregime]

*BLNLengthofbodyno

*Notrequiredinsubsonicspeedregime

*BLALengthofcylindricalafterbodygment,=0.0fornoalone

*orno-tailconfiguration

*Notrequiredinsubsonicspeedregime

*DSNobluntnessdiameter,zeroforsharpnobodies

*[Hypersonicspeedregimeonly]

*ITYPE1.0=straightwing,noarearule

*2.0=sweptwing,noarearule(default)

*3.0=sweptwing,arearule

*METHOD1.0=Uexistingmethods(default)

*2.0=UJorgennmethod

$BODYNX=8.0,

X(1)=0.0,1.0,2.7,6.0,8.8,28.5,39.4,44.8,

6

R(1)=0.0,1.25,2.1,2.7,2.76,2.7,1.25,0.0,

ZU(1)=3.5,4.3,4.8,5.5,7.4,7.4,6.5,5.7,

ZL(1)=3.5,2.5,2.25,2.1,2.0,2.2,4.3,5.7,

BNOSE=1.0,BLN=8.8,

BTAIL=1.0,BLA=19.7,

ITYPE=1.0,METHOD=1.0$

**********************************

*Wingplanformvariablespg37-38

**********************************

*CHRDRChordroot

*uiredforstraight

*taperedplanform.

*CHRDTPTipchord

*SSPNSemi-spantheoreticalpanelfromtheoreticalrootchord

*SSPNESemi-spanexpodpanel,Seediagramonpg37.

*uiredforstraight

*taperedplanform.

*SAVSIInboardpanelsweepangle

*SAVSOOutboardpanelsweepangle

*CHSTATReferencechordstationforinboardandoutboardpanel

*sweepangles,fractionofchord

*TWISTATwistangle,negativeleadingedgerotateddown(from

*expodroottotip)

*SSPNDDSemi-spanofoutboardpanelwithdihedral

*DHDADIDihedralangleofinboardpanel

*DI=DHDADOonly

*inputDHDADI

*TYPE1.0-Straighttaperedplanform

*2.0-Doubledeltaplanform(aspectratio<=3)

*3.0-Crankedplanform(aspectratio>3)

$WGPLNFCHRDR=9.4,CHRDTP=3.01,

SSPN=25.85,SSPNE=23.46,

SAVSI=1.3,

CHSTAT=0.25,TWISTA=-3.0,

DHDADI=3.6,

TYPE=1.0$

**********************************************

*WingSectionalCharacteristicsParameters*pg39-40

7

**********************************************

*Thectionaerodynamiccharacteristicsforthesurfacesare

*inputusingeitherthectionalcharacteristicsnamelistsWGSCHR,

*HTSCHR,VTSCHRandVFSCHRand/l

*characteristicsareassummedconstantforeachpaneloftheplanform.

*

*Toavoidhavingtoinputalltheairfoilctionalcharacteristics,

*inColumn1.

*

*NACAxyzzzzzz

*

*where:

*column1-4NACA

*5anydeliminator

*6W,H,V,orFPlanformforwhichtheairfoil

*designationapplies:Wing,Horizontal

*tail,Verticaltail,orVentralfin.

*7anydeliminator

*81,4,5,6,STypeofairfoilction:1-ries,

*4-digit,5-digit,6-ries,orSupersonic

*9anydeliminator

*10-80Designation,columnsarefreeformat,blanksareignored

*

*TOVCMaximumairfoilctionthicknessfractionofchord

*[Requiredinput,ursuppliedorcomputedbyairfoil

*ctionmoduleifairfoildefinedwithNACAcardor

*ctioncoordinates]

*DELTAYDifferencebetweenairfoilordinatesat6%and15%chord,

*percentchord(%correct???)

*[Requiredinput,ursuppliedorcomputedbyairfoil

*ctionmoduleifairfoildefinedwithNACAcardor

*ctioncoordinates]

*XOVCChordlocationofmaximumairfoilthickness,fractionofchord

*[Requiredinput,ursuppliedorcomputedbyairfoil

*ctionmoduleifairfoildefinedwithNACAcardor

*ctioncoordinates]

*CLIAirfoilctiondesignliftcoefficient

*[Requiredinput,ursuppliedorcomputedbyairfoil

*ctionmoduleifairfoildefinedwithNACAcardor

*ctioncoordinates]

*ALPHAIAngleofattackatctiondesignliftcoefficient,deg

*[Requiredinput,ursuppliedorcomputedbyairfoil

*ctionmoduleifairfoildefinedwithNACAcardor

*ctioncoordinates]

8

*CLALPAAirfoilctionliftcurveslopedCl/dAlpha,perdeg(array20)

*[Requiredinput,ursuppliedorcomputedbyairfoil

*ctionmoduleifairfoildefinedwithNACAcardor

*ctioncoordinates]

*CLMAXAirfoilctionmaximumliftcofficient(array20)

*[Requiredinput,ursuppliedorcomputedbyairfoil

*ctionmoduleifairfoildefinedwithNACAcardor

*ctioncoordinates]

*CMOSectionzeroliftpitchingmomentcoefficient

*[Requiredinput,ursuppliedorcomputedbyairfoil

*ctionmoduleifairfoildefinedwithNACAcardor

*ctioncoordinates]

*LERIAirfoilleadingedgeradius,fractionofchord

*[Requiredinput,ursuppliedorcomputedbyairfoil

*ctionmoduleifairfoildefinedwithNACAcardor

*ctioncoordinates]

*LERORLEforoutboardpanel,fractionofchord

*[Requiredinput].

*Notrequiredforstraighttaperedplanforms.

*CAMBERCamberedairfoilflagflag

*[Requiredinput,ursuppliedorcomputedbyairfoil

*ctionmoduleifairfoildefinedwithNACAcardor

*ctioncoordinates]

*TOVCOt/cforoutboardpanel

*[Requiredinput,ursuppliedorcomputedbyairfoil

*ctionmoduleifairfoildefinedwithNACAcardor

*ctioncoordinates]

*Notrequiredforstraighttaperedplanforms.

*XOVCO(x/c)maxforoutboardpanel

*[Requiredinput,ursuppliedorcomputedbyairfoil

*ctionmoduleifairfoildefinedwithNACAcardor

*ctioncoordinates]

*Notrequiredforstraighttaperedplanforms.

*CMOTCmoforoutboardpanel

*[Requiredinput,ursuppliedorcomputedbyairfoil

*ctionmoduleifairfoildefinedwithNACAcardor

*ctioncoordinates]

*Notrequiredforstraighttaperedplanforms.

*CLMAXLAirfoilmaximumliftcoefficientatmach=0.0

*[Requiredinput,ursuppliedorcomputedbyairfoil

*ctionmoduleifairfoildefinedwithNACAcardor

*ctioncoordinates]

*CLAMOAirfoilctionliftcurveslopeatMach=0.0,perdeg

*[edinput

9

*fortransonicspeedregime,ursuppliedorcomputedif

*NACAcardsupplied]

*TCEFFPlanformeffectivethicknessratio,fractionofchord

*[edinput

*fortransonicspeedregime,ursuppliedorcomputedif

*NACAcardsupplied]

*KSHARPWave-dragfactorforsharp-nodairfoilction,not

*inputforround-nodairfoils

*[edinput

*fortransonicspeedregime,ursuppliedorcomputedif

*NACAcardsupplied]

*SLOPEAirfoilsurfaceslopeat0,20,40,60,80and100%chord,deg.

*Positivewhenthetangentinterctsthechordplaneforward

*ofthereferencechordpoint

*[edinput

*fortransonicspeedregime,ursuppliedorcomputedif

*NACAcardsupplied]

*ARCLAspectratioclassification(etable9,pg41)

*[Optionalinput]

*XACSectionAerodynamicCenter,fractionofchord

*[Optionalinput,computedbyairfoilctionmoduleifairfoil

*definedwithNACAcardorctioncoordinates]

*DWASHSubsonicdownwashmethodflag

*=1.0uDATCOMmethod1

*=2.0uDATCOMmethod2

*=3.0uDATCOMmethod3

*Supersonic,uDATCOMmethod2

*[Optionalinput]

*Seefigure9onpage41.

*YCMAirfoilmaximumcamber,fractionofchord

*[Requiredinput,ursuppliedorcomputedbyairfoil

*ctionmoduleifairfoildefinedwithNACAcardor

*ctioncoordinates]

*CLDConicalcamberdesignliftcoefficientforM=1.0design

*eNACARMA55G19(defaultto0.0)

*[Requiredinput]

*TYPEINTypeofairfoilctioncoordinatesinputforairfoil

*ctionmodule

*=1.0upperandlowersurfacecoordinates(YUPPERandYLOWER)

*=2.0Meanlineandthicknessdistribution(MEANandTHICK)

*[Optionalinput]

*NPTSNumberofctionpointsinput,max=50.0

*[Optionalinput]

*XCORDAbscissasofinputspoints,TYPEIN=1.0or2.0,XCORD(1)=0.0

10

*XCORD(NPTS)=1.0required.

*[Optionalinput]

*YUPPEROrdinatesofuppersurface,TYPEIN=1.0,fractionofchord,and

*requiresYUPPER(1)=0.0andYUPPER(NPTS)=0.0

*[Optionalinput]

*YLOWEROrdinatesoflowersurface,TYPEIN=1.0,fractionofchord,

*andrequiresYLOWER(1)=0.0andYLOWER(NPTS)=0.0

*[Optionalinput]

*MEANOrdinatesofmeanline,TYPEIN=2.0,fractionofchord,and

*requiresMEAN(1)=0.0andMEAN(NPTS)=0.0

*[Optionalinput]

*THICKThicknessdistribution,TYPEIN=2.0,fractionofchord,and

*requiresTHICK(1)=0.0andTHICK(NPTS)=0.0

*[Optionalinput]

*

*Note:Onlyoneairfoilctioncanbedefined,sowe'regoingto

*ualairfoilisa

*5-riesmodified(23016-5),butI'mnotreallysurehow

*togetthe-5partin,andwhatitmeans,andwherethemax

*isNACA23012.

*

NACAW523014

SAVE

******************************************

*SymetricalFlapDeflectionparameters

******************************************

*DATCOMpg47states:

*

*"Ingeneral,theeightflaptypesdefinedusingSYMFLP

*(variableFTYPE)areassumedtobelocatedonthemost

*aftliftingsurface,eitherhorizontaltailorwingif

*ahorizontaltailisnotdefined."

*

*FTYPEFlaptype

*1.0Plainflaps

*2.0Singleslottedflaps

*3.0Fowlerflaps

*4.0Doubleslottedflaps

*5.0Splitflaps

11

*6.0Leadingedgeflap

*7.0Leadingedgeslats

*8.0Krueger

*NDELTANumberofflaporslatdeflectionangles,maxof9

*

*DELTAFlapdeflectionanglesmeasuredstreamwi

*(NDELTAvaluesinarray)

*PHETETangentofairfoiltrailineedgeanglebadonordinatesat

*90and99percentchord

*PHETEPTangentofairfoiltrailingedgeanglebadonordinatesat

*95and99percentchord

*CHRDFIFlapchordatinboardendofflap,measuredparallelto

*longitudinalaxis

*CHRDFOFlapchordatoutboardendofflap,measuredparallelto

*longitudinalaxis

*SPANFISpanlocationofinboardendofflap,measuredperpendicular

*toverticalplaneofsymmetry

*SPANFOSpanlocationofoutboardendofflap,measuredperpendicular

*toverticalplaneofsymmetry

*CPRMEITotalwingchordatinboardendofflap(translatingdevices

*only)measuredparalleltolongitudinalaxis

*(NDELTAvaluesinarray)

*Single-slotted,Fowler,Double-slotted,leading-edge

*slats,Kruegerflap,jetflap

*CPRMEOTotalwingchordatoutboardendofflap(translatingdevices

*only)measuredparalleltolongitudinalaxis

*(NDELTAvaluesinarray)

*Single-slotted,Fowler,Double-slotted,leading-edge

*slats,Kruegerflap,jetflap

*CAPINS(double-slottedflapsonly)

*CAPOUT(double-slottedflapsonly)

*DOSDEF(double-slottedflapsonly)

*DOBCIN(double-slottedflapsonly)

*DOBCOT(double-slottedflapsonly)

*SCLDIncrementinctionliftcoefficientdueto

*deflectingflaptoangleDELTA[i](optional)

*(NDELTAvaluesinarray)

*SCMDIncrementinctionpitchingmomentcoefficientdueto

*deflectingflaptoangleDELTA[i](optional)

*(NDELTAvaluesinarray)

*CBAveragechordofthebalance(plainflapsonly)

*TCAveragethicknessofthecontrolathingeline

*(plainflapsonly)

*NTYPETypeofno

12

*1.0Roundnoflap

*2.0Ellipticnoflap

*3.0Sharpnoflap

*JETFLPTypeofflap

*1.0Purejetflap

*2.0IBF

*3.0EBF

*CMUTwo-dimensionaljeteffluxcoefficient

*DELJETJetdeflectionangle

*(NDELTAvaluesinarray)

*EFFJETEBFEffectivejetdeflectionangle

*(NDELTAvaluesinarray)

$SYMFLPFTYPE=2.0,NDELTA=9.0,

DELTA(1)=0.0,5.0,10.0,15.0,20.0,25.0,30.0,35.0,40.0,

PHETE=0.0522,PHETEP=0.0391,

CHRDFI=2.0,CHRDFO=1.6,

SPANFI=5.78,SPANFO=15.3,

CPRMEI(1)=8.1,8.1,8.2,8.2,8.3,8.3,8.3,8.4,8.4,

CPRMEO(1)=3.7,3.7,3.8,3.8,3.9,3.9,3.9,4.0,4.0,

NTYPE=1.0$

*Atthispoint,wearegoingtoterminatethecasothatwecanget

*'tsavethisdata,asweare

*alsogoingtodocontrolsurfacesonthehorizontaltail.

CASEIDFLAPS:CitationIIModel550Aircraft

NEXTCASE

*************************************************************

*AsymmetricalControlDeflectionparameters:Ailerons

*************************************************************

*STYPEType

*1.0Flapspoileronwing

*2.0Plugspoileronwing

*3.0Spoiler-slot-deflectiononwing

*4.0Plainflapaileron

*5.0Differentiallydeflectedallmoveablehorizontaltail

*NDELTANumberofcontroldeflectionangles,requiredforallcontrols,

*maxof9

*DELTALDefelctionangleforlefthandplainflapaileronorleft

13

*handpanelallmoveablehorizontaltail,measuredin

*verticalplaneofsymmetry

*DELTARDefelctionangleforrighthandplainflapaileronorright

*handpanelallmoveablehorizontaltail,measuredin

*verticalplaneofsymmetry

*SPANFISpanlocationofinboardendofflaporspoilercontrol,

*measuredperpendiculartoverticalplaneofsymmetry

*SPANFOSpanlocationofoutboardendofflaporspoilercontrol,

*measuredperpendiculartoverticalplaneofsymmetry

*PHETETangentofairfoiltrailingedgeanglebadonordinates

*atx/c-0.90and0.99

*CHRDFIAileronchordatinboardendofplainflapaileron,

*measuredparalleltolongitudinalaxis

*CHRDFOAileronchordatoutboardendofplainflapaileron,

*measuredparalleltolongitudinalaxis

*DELTADProjectedheightofdeflector,spoiler-slot-deflector

*control,fractionofchord

*DELTASProjectedheightofspoiler,flapspoiler,plugspoilerand

*spoiler-slot-deflectorcontrol;fractionofchord

*XSOCDistancefromwingleadingedgetospoilerlipmeasured

*paralleltostreamwiwngchord,flapandplugspoilers,

*fractionofchord

*XSPRMEDistancefromwingleadingedgetospoilerhingeline

*measuredparalleltostreamwichord,flapspoiler,

*plugspoilerandspoiler-slot-deflectorcontrol,fraction

*ofchord

*HSOCProjectedheightofspoilermeasuredfromandnormalto

*airfoilmeanline,flapspoiler,plugspoilerandspoiler-

*slot-reflector,fractionofchord

$ASYFLPSTYPE=4.0,NDELTA=9.0,

DELTAL(1)=-32.0,-20.0,-10.0,-5.0,0.0,5.0,10.0,20.0,32.0,

DELTAR(1)=32.0,20.0,10.0,5.0,0.0,-5.0,-10.0,-20.0,-32.0,

SPANFI=15.2,SPANFO=24.0,

PHETE=0.05228,

CHRDFI=1.87,CHRDFO=1.2$

*Terminatesthereadingofinputcardsandbeginxecutionof

*taaredestroyedfollowingexecutionofaca,

*unlesstheSAVEcardisprent.

CASEIDAILERONS:CitationIIModel550Aircraft

SAVE

14

NEXTCASE

*************************************************

*HorizontalTailSectionalCharacteristicspg39-40

*************************************************

*Samebuildupaswing,ifyou'dliketouthatinstead.

NACAH40010!Citationis0010atroot,0008attip

*********************************************

*HorizontalTailplanformvariablespg37-38

*********************************************

*CHRDTPTipchord

*uiredforstraight

*taperedplanform.

*SSPNESemi-spanexpodpanel

*SSPNSemi-spantheoreticalpanelfromtheoreticalrootchord

*CHRDBPChordatbreakpoint

*CHRDRChordroot

*SAVSIInboardpanelsweepangle

*CHSTATReferencechordstationforinboardandoutboardpanel

*sweepangles,fractionofchord

*TWISTATwistangle,negativeleadingedgerotateddown(from

*expodroottotip)

*SSPNDDSemi-spanofoutboardpanelwithdihedral

*DHDADIDihedralangleofinboardpanel

*DI=DHDADOonly

*inputDHDADI

*TYPE1.0-Straighttaperedplanform

*2.0-Doubledeltaplanform(aspectratio<=3)

*3.0-Crankedplanform(aspectratio>3)

*SHBPortionoffulagesideareathatliesbetweenMachlines

*originatingfromleadingandtrailingedgesofhorizontal

*tailexpodrootchord(array20).

*Onlyrequiredforsupersonicandhypersonicspeedregimes.

*SEXTPortionofextendedfueslagesideareathatliesbetween

*Machlinesoriginatingfromleadingandtrailingedgesof

*horizontaltailexpodrootchord(array20)

*Onlyrequiredforsupersonicandhypersonicspeedregimes.

15

*RLPHLongitudinaldistancebetweenCGandcentroidofSh(B)

*positiveaftofCG

*Onlyrequiredforsupersonicandhypersonicspeedregimes.

$HTPLNFCHRDR=4.99,CHRDTP=2.48,

SSPN=9.42,SSPNE=9.21,

SAVSI=5.32,

CHSTAT=0.25,TWISTA=0.0,

DHDADI=9.2,

TYPE=1.0$

******************************************

*VerticalTailplanformvariablespg37-38

******************************************

*CHRDTPTipchord

*SSPNOPSemi-spanoutboardpanel

*SSPNESemi-spanexpodpanel

*SSPNSemi-spantheoreticalpanelfromtheoreticalrootchord

*CHRDBPChordatbreakpoint

*CHRDRChordroot

*SAVSIInboardpanelsweepangle

*SAVSOOutboardpanelsweepangle

*CHSTATReferencechordstationforinboardandoutboardpanel

*sweepangles,fractionofchord

*TYPE1.0-Straighttaperedplanform

*2.0-Doubledeltaplanform(aspectratio<=3)

*3.0-Crankedplanform(aspectratio>3)

*SVWBPortionofexpodverticalpanelareathatliesbetween

*Machlinemanatingfromleadingandtrailingedgesof

*wingexpodrootchord(array20)

*Onlyrequiredforsupersonicandhypersonicspeedregimes.

*SVBAreaofexpodverticalpanelnotinfluencedbywingor

*horizontaltail(array20)

*Onlyrequiredforsupersonicandhypersonicspeedregimes.

*SVHBPortionofexpodverticalpanelareathatliesbetweenMach

*linemanatingfromleadingandandtrailingedgesof

*horizontaltailexpodrootchord(array20)

*Onlyrequiredforsupersonicandhypersonicspeedregimes.

$VTPLNFCHRDTP=3.63,SSPNE=8.85,SSPN=9.42,CHRDR=8.3,

SAVSI=32.3,CHSTAT=0.25,TYPE=1.0$

16

******************************************

*VerticalFinplanformvariablespg37-38

******************************************

*CHRDRChordroot

*CHRDBPChordatbreakpoint

*CHRDTPTipchord

*SSPNOPSemi-spanoutboardpanel

*SSPNESemi-spanexpodpanel

*SSPNSemi-spantheoreticalpanelfromtheoreticalrootchord

*SAVSIInboardpanelsweepangle

*CHSTATReferencechordstationforinboardandoutboardpanel

*sweepangles,fractionofchord

*DI=DHDADOonly

*inputDHDADI

*DI=DHDADOonly

*inputDHDADI

*TYPE1.0-Straighttaperedplanform

*2.0-Doubledeltaplanform(aspectratio<=3)

*3.0-Crankedplanform(aspectratio>3)

*SVWBPortionofexpodverticalpanelareathatliesbetween

*Machlinemanatingfromleadingandtrailingedgesof

*wingexpodrootchord(array20)

*Onlyrequiredforsupersonicandhypersonicspeedregimes.

*SVBAreaofexpodverticalpanelnotinfluencedbywingor

*horizontaltail(array20)

*Onlyrequiredforsupersonicandhypersonicspeedregimes.

*SVHBPortionofexpodverticalpanelareathatliesbetweenMach

*linemanatingfromleadingandandtrailingedgesof

*horizontaltailexpodrootchord(array20)

*Onlyrequiredforsupersonicandhypersonicspeedregimes.

$VFPLNFCHRDR=11.8,CHRDTP=0.0,CHSTAT=0.0,DHDADO=0.0,

SAVSI=80.0,SSPN=2.3,SSPNE=2.1,TYPE=1.0$

***********************************

*ElevatorDeflectionparameters

***********************************

*FTYPEFlaptype

17

*1.0Plainflaps

*2.0Singleslottedflaps

*3.0Fowlerflaps

*4.0Doubleslottedflaps

*5.0Splitflaps

*6.0Leadingedgeflap

*7.0Leadingedgeslats

*8.0Krueger

*NDELTANumberofflaporslatdeflectionangles,maxof9

*DELTAFlapdeflectionanglesmeasuredstreamwi

*(NDELTAvaluesinarray)

*PHETETangentofairfoiltrailineedgeanglebadonordinatesat

*90and99percentchord

*PHETEPTangentofairfoiltrailingedgeanglebadonordinatesat

*95and99percentchord

*CHRDFIFlapchordatinboardendofflap,measuredparallelto

*longitudinalaxis

*CHRDFOFlapchordatoutboardendofflap,measuredparallelto

*longitudinalaxis

*SPANFISpanlocationofinboardendofflap,measuredperpendicular

*toverticalplaneofsymmetry

*SPANFOSpanlocationofoutboardendofflap,measuredperpendicular

*toverticalplaneofsymmetry

*CPRMEITotalwingchordatinboardendofflap(translatingdevices

*only)measuredparalleltolongitudinalaxis

*(NDELTAvaluesinarray)

*Single-slotted,Fowler,Double-slotted,leading-edge

*slats,Kruegerflap,jetflap

*CPRMEOTotalwingchordatoutboardendofflap(translatingdevices

*only)measuredparalleltolongitudinalaxis

*(NDELTAvaluesinarray)

*Single-slotted,Fowler,Double-slotted,leading-edge

*slats,Kruegerflap,jetflap

*CAPINS(double-slottedflapsonly)(NDELTAvaluesinarray)

*CAPOUT(double-slottedflapsonly)(NDELTAvaluesinarray)

*DOSDEF(double-slottedflapsonly)(NDELTAvaluesinarray)

*DOBCIN(double-slottedflapsonly)

*DOBCOT(double-slottedflapsonly)

*SCLDIncrementinctionliftcoefficientdueto

*deflectingflaptoangleDELTA[i](optional)

*(NDELTAvaluesinarray)

*SCMDIncrementinctionpitchingmomentcoefficientdueto

*deflectingflaptoangleDELTA[i](optional)

*(NDELTAvaluesinarray)

18

*CBAveragechordofthebalance(plainflapsonly)

*TCAveragethicknessofthecontrolathingeline

*(plainflapsonly)

*NTYPETypeofno

*1.0Roundnoflap

*2.0Ellipticnoflap

*3.0Sharpnoflap

*JETFLPTypeofflap

*1.0Purejetflap

*2.0IBF

*3.0EBF

*CMUTwo-dimensionaljeteffluxcoefficient

*DELJETJetdeflectionangle

*(NDELTAvaluesinarray)

*EFFJETEBFEffectivejetdeflectionangle

*(NDELTAvaluesinarray)

$SYMFLPFTYPE=1.0,

NDELTA=9.0,DELTA(1)=-20.0,-15.0,-10.0,-5.0,0.0,5.0,10.0,13.0,16.0,

PHETE=0.0522,PHETEP=0.0523,

CHRDFI=1.94,CHRDFO=1.03,

SPANFI=0.7,SPANFO=9.21,

CB=0.84,TC=0.3,NTYPE=1.0$

**************************************

*VerticalTailSectionalCharacteristicspg39-40

**************************************

*Samebuildupaswing,ifyou'dliketouthatinstead.

NACAV40012!Citationis0012atroot,0008attip

**********************************************

*VentralFinSectionalCharacteristicspg39-40

**********************************************

*Samebuildupaswing,ifyou'dliketouthatinstead.

NACAF40012!GuessittobethesameasverticaltailforCitation.

19

*********************************

*JetPowerEffectsparameterspg51

*********************************

*

*IMPORTANTNOTE:TheeffectsofPOWERareincludingintheDATCOM

*outputfile(hisca),atthebottomwherethe

*totalaircraftparametersarelisted(CD,CL,CM,etc.).Forthe

*Datcom+outputfiles,thepowereffectsareremovedandprented

*(ifnotnow,theywillbesomeday)y,

*youcaninterpolatetogetpowerttingsbetweenzero(off)and

*whateverthemaximumthatyouspecifyhere.

*

*AIETLJAngleofincidenceofenginethrustline,deg

*AMBSTPAmbientstaticpressure

*AMBTMPAmbienttemperature,deg

*JEALOCAxiallocationofjetengineexit,feet

*JEANGLJetexitangle

*JELLOCLaterallocationofjetengine,ft

*JERADRadiusofjetexit

*JESTMPJetexitstatictemperature

*JETOTPJetexittotalpressure

*JEVELOJetexitvelocity

*JEVLOCVerticallocationofjetengineexit,feet

*JIALOCAxiallocationofjetengineinlet,feet

*JINLTAJetengineinletarea,squarefeet

*NENGSJNumberofengines(1or2)

*THSTCJThrustcoefficient2T/(PV^2*Sref)

*Setthisto0tokeeppowereffectsoutofcoefficients.

$JETPWRNENGSJ=2.0,AIETLJ=2.0,THSTCJ=0.0,

JIALOC=25.8,JELLOC=4.33,JEVLOC=5.625,

JEALOC=33.3,JINLTA=2.243,

AMBTMP=59.7,AMBSTP=2116.8,JERAD=0.755$

CASEIDTOTAL:CitationIIModel550Aircraft