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ofgravitywasdeterminedbyinterpolationusingthe vestandardmasssetsasexplainedinthenextsection.TheAUTOFLAP

FLAGwasoff,soQuasi-SteadyAeroElastic(QSAE)incrementswereincorporated.The

MATLABOptimizationToolboxconstrainedoptimizationroutineconstr.mwasusedtovarythetrimvariablestoachievethetrimconditions.Oncetrimwasachieved,thederivativesandwereestimatedusingacentraldifferencederivativeapproximationwithdeg.,furtherutilizingrefhsim3

lin.mfrom[4].LateralandlongitudinaleigenvalueswerecalculatedbyapplyingMAT-LABbuilt-infunctioneigtosubblocksofthelinearsystemmatrix.

TrimDetails

Inalltrimruns,thethrustmultiplierwassetto1.09,sothatmaximumpoweravailable

was109%ofnominalmaximum.ThiswassuggestedbyDr.ChrisGraceyofLaRCbasedonhisexperiencewithcalculatingfueloptimaltrajectories.

Atall ightconditions,nominalXandZpositionsofthecenterofgravityweredetermined

bylinearinterpolationusinggrossweightastheindependentvariableandusingthesimulationmasssetsfrom[2,Table3.1-1,Page3-2].Therelevantdataare(Z-CGdatacomefromaBoeing-suppliedFORTRANsubroutineDATAstatement):

MassSet

GrossWeight(lb)

XCGBS(in)

ZCGWL(in)

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