CurrentPlansforTestingHL-CRMin14x22

JudiHannon,JohnLin,DaveLockardNASALangleyResearchCenter

3rd HighLiftPredictionWorkshopDenver,COJune3-4,2017

CRMsAreMultiplying

• CRM:CommonResearchModel• usedforDPWworkshops

• HL-CRM:High-LiftCommonResearchModel• CHL:ConventionalHighLift• SHL:SimplifiedHighLift

• NLFCRM:NaturalLaminarFlowCommonResearchModel• 13.5ARCRM:13.5AspectRatioCommonResearchModel• ...

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HL-CRMProjectPlanandSchedule

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• Phase 1 Model fabrication to be completed by 3/30/18 • ~32 weeks of tunnel occupation time at 14x22

(4/26/18 to 1/29/19)• Aerodynamic test – 1st half

Ø Conventional (baseline) configurationØ Simple hinged flap with AFC on flap LE

• Acoustic test – 2nd half (noise reduction)Ø Conventional configuration (fixed rigging)

Ø With and without landing gearØ Slat cove-filler and slat gap-fillerØ Flap and slat side-edge treatments

FY16 FY17 FY18 FY19 FY20Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4

HL-CRM Wind Tunnel Testing

Fab/Deliver Semispan Model (14x22)

HL-CRM Test (14x22), ~32 weeks

Design Semispan Model (14x22)

Analysis & Documentation of 14x22 Test

NASALangley14x22FootSubsonicWindTunnel(14x22)

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Acoustic test section

Aerodynamic test section

Acoustic array

• Semispan (1/10th scale) model• M∞ = 0.20 for landing configurations (ReC = 3.27x106 )• M∞ = 0.26 for takeoff configurations (ReC = 4.24x106 )

Acoustic array

• 10% semispan model • 115.68 inches semispan• 3.5 inches standoff• 68% tunnel span (vertical)

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• Model center moved slightly aft from turntable center

• Fuselage extends past turntable & past end of cart

• Fuselage length = 20.59 feet

(top view)

(side view)

Semispan HL-CRMin14x22– AerodynamicSetup

HL-CRMFeatures

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• ModularcomponentsØ Replaceableflap(with

AFC-enabledhingedflaps)Ø Replaceableslats(withnoise

reductionconceptslats)andslattipsØ RemovableenginenacelleØ ProvisionforaileronØ WheelwellØ ReplaceablewingtipØ FlapedgenoisetreatmentØ RemovablelandinggearNotpicturedØ Removablehorizontaltail

• SlatbracketsØ inboard:3Ø outboard:12Ø realisticwidth,U-shape

• Flapbrackets/fairingsØ inboard:1external,1infuselageØ outboard:2

Center spar

Provision for flap edge noise reduction treatment

Provision for replaceable wingtip

Provision for aileron

Removable engine nacelle

Wheel wellProvision for slat edge noise reduction treatments

ModelTesting– AerodynamicTestSection

• ConventionalHighLift(goalisreasonablebaselineforSHL)• landingconfiguration

• M=0.200,Rec =~3.2million• startwithflaps=37deg;slats=30deg• otherriggings??

• nacelle/pylon??• horizontaltail??• artificiallytripfortransitionorallownaturaltransition??

• SimplifiedHighLiftwithActiveFlowControl(AFC)• landingconfigurationfocusedaroundAoA =8deg,somethroughCLmax

• hingedflaps~50deg;conventionalslats• variousAFCconcepts

• NoiseReductionConcepts• LimitedtestingtoCLmax toassessaerodynamicperformance

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Acoustic array

PlannedMeasurementsforAerodynamics

• Forces/moments• Surfacestaticpressures• Unsteadysurfacepressure• Afewonthemainelementandaroundtheoutboardflapedge

• SomeontheAFCflap• Modeldeformation– photogrammetry• Transitiondetection– infraredcameras• In-wallacousticarrayforalimitednumberofconfigurations

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Acoustic array

ModelTesting– AcousticTestSection

• NoiseReductionConcepts• conventionallandingconfiguration

(fixedrigging)• withandwithoutlandinggear• withandwithoutnacelle/pylon

• slatcove-fillerandslatgap-filler• flapandslatedgetreatments

• SimplifiedHigh-LiftwithActiveFlowControl(AFC)• iftimepermits

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Acoustic array

PlannedMeasurementsforAcoustics

• 97channelmicrophonearray• Individualpolemountedmicrophones• Forces/moments• Surfacestaticpressures• Reducednumberonslat

• Unsteadysurfacepressure• Extensiveonslat• Afewonthemainelementandaroundtheoutboardflapedge

• Modeldeformation– photogrammetryandstraingaugesonslatnoise-reductiondevices

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Acoustic array

FutureTesting

• NASAproject(s)planninginprogress• Collaborativediscussionsinprogress• Possibilities:• localizedactiveflowcontrolconcepts• noisereductionconcepts• severalotherpossibilitiesaredesignedintomodel

• SuggestionforHiLiftPW:• startdiscussionsaboutwhatcanbedonewiththeHL-CRMtofurtheradvancegoalsofHiLiftPW (seemslikewearestillworkingthefirstoffourstatedobjectives)

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HiLiftPW Objectives

• Assessthenumericalpredictioncapability(meshing,numerics,turbulencemodeling,high-performancecomputingrequirements,etc.)ofcurrent-generationCFDtechnology/codesforswept,medium/high-aspectratiowingsinlanding/take-off(high-lift)configurations

• DeveloppracticalmodelingguidelinesforCFDpredictionofhigh-liftflowfields

• Advancetheunderstandingofhigh-liftflowphysicstoenabledevelopmentofmoreaccuratepredictionmethodsandtools

• EnhanceCFDpredictioncapabilitytoenablepracticalhigh-liftaerodynamicdesignandoptimization

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