NATIONALADVISORYCOMMITTEE FORAERONAUTICS/67531/metadc... · cm nationaladvisorycommittee foraeronautics technical note 4178 low-speedcascadeinvestigationofcompressorblades havingloadedleadinge~es

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NATIONALADVISORYCOMMITTEEFORAERONAUTICS

TECHNICAL NOTE 4178

LOW-SPEEDCASCADEINVESTIGATIONOFCOMPRESSORBLADES

HAVINGLOADEDLEADINGE~ES

By JamesC. Emery

1,●

LangleyAeronauticalLaboratoryLangleyField, Va.

WashingtonJanuary1958

Amwc

TECHLIBRARYKAFB,NM

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Illlllllllilll{tiirllllllNATIONALADVISORYCOMMITTEEFORJ$XRONAUTIC tiobb8qB”

TECHNICALNOTE4178

IQW-SPEEDCASCADEINVESTIGATIONOFCOMPRESSORBLADES

HAVINGIOADEDLEADINGEEG@

By JamesC.wry

WMMARY

Six-percent-thickNACA63-seriescompressor-bladesectionshatingaloaded-leading-edgeA@% meanlinehavebeeninvestigatedsystematicallyina two-dimensionalporous-wallcascadeovera rs.ngeofReynoldsnumberfrom160,000to385,000.Bladescamberedtohaveisolated-airfoilliftcoefficientsof0.6,1.2, 1.8, and2.4weretestedovertheusableangle-of-attackrangeat inlet-airanglesof ~“, 45°,and60°andsolidifiesof1.0and1.5.

A comparisonwithdataofNACATechnicalNote391.6showsthattheangle-of-attackoperatingrsmgeis@ to 6° lessthantherangefortheuniformlyloadedsection;however,thewakelossesneardesignangleofattackareslightlylowerthanthosefortheuniformlyloadedsection.Exceptforhighlycanberedbladesathighinletangles,theNACA63-(~zoA4%5)06compressor-bladesectionsarecapableofmoreefficient

9

u’

●

operationformoderate-speedstisoniccompressorsat designangleofattackthanaretheNACA@-(CzoA1o)10ortheNACA65-(c20&~)10compressor-bladesections,where %0 inthedesignationis thedesignliftcoefficientoftheisolatedairfoil.In contrastwiththeothersections,theloaded-leading-edgesectionsarecapableofoperatingefficientlyatthelowerReynoldsntiers.

INTRODUCTION

Systematiclow-speedcascadedatafortheNACA~-seriesccmrpressor-bladesectionssrepresentedinreference1 fora widerangeof cascadeconfigurations.Thesedata,however,arelimitedtotheuniformlyloadedmeanline. Inhigh-speedcompressors,blademeanlinesotherthanthose

l-SupersedesrecentlydeclassifiedNACAResearchMemorandumL55J05,“Low-SpeedCascadeInvestigationof LoadedLeading-E&eCompressorBlades,”by JsmesC.Emery,1956.

.

2 NACATN 4178b

foruniformloadareofinterest.Reference2 presentstheresultsofasystematicvariationinmean-lineloadingforNACA65-seriescompressor-

?

bladesectionshavingtheA@4b andA#~ meanlines,whichshifttheloadingtowardthetrailingedge,andtheA614meanlinewhichshiftstheloadingtowardtheleadingedge.Additionaldatafora loaded-leading-edgemeanlineA4K6wereobtainedinaminvestigationto developaseriesof 6-percent-thickguide-vaneprofiles(ref.3) suitableforoperationathighinletMachnumbers.ThisconsiderationledtoadeparturefrcmtheNACA65-seriesthiclmessdistributiontotheNACA63-seriesthicknessdistributionwhichhasa moreforwardlocationofmaximumthickness.At thessmetime,thethicknesswasreducedfrom10to 6 percent.Thiscombinationofmean-lineloading,thicknessdistribution,andthicknessprovidedfavorableblade-passage-areadis-tributionsforhigh-speedcompressorswherechokingguide-vanepassageswasa possibility.Theresultslimitedto an inlet-airangleofOO.

Someexplorato~testsoftheguide-vanebladeairanglesintherangeof interestfoccompressorsturningandlowdrag. Thepurposeofthispaperis

oftheflowintheofreference3 are

sectionsatinl.et-showedhightopresentdata

obtain&intestsofthe6-per&nt-thickNA6A-63-series-withA4~ mean-

M.neloadingat inlet-ahanglesof30°,45°,and600,eachat solidifiesof1.0and1.5inthelow-speedpotious-wallcascade.Carpetplotsofthe63-(cz#4~)06datasndcomparisonsofthesedatawithdataforthe

65-(12A21~)10and65-(l~lo)10profilesme ticlud~.

SYMBOLS

c bladechord,ft

cdl sectiondragcoefficientbasedonupstreemdynamicpressure

C21 sectionliftcoefficientbasedonupstreamdynamicpressure

Czo camber,expressedasdesignliftcoeffici~tof isolatedairfoil

cW1 wakemomentum-differencecoefficientbasedonupstream“-dynsmicpressure

L/D lift-dragratio

P totalpressure

P. staticpressure

●

v

.

3NACATN 4178&

q -C pressured

R Reynoldsnumberbasedonbladechordandenteringvelocity

P- Pzs pressurecoefficient,—

ql

a anglebetweentheinletflowandthebladechord,deg

$ inlet-airangle,anglebetweentheinlet-flowdirect~onandtheperpendiculartothecascade,deg

8 flowturningangle,deg

G solidity,chordofbladesdividedby tangentialspacing

% resultantpressurecoefficient;differencebetweenlocalupper-andlower-surfacepressurecoefficients

ATq

ratioofblade-passagethroatareatoareaofupstreamflow

x chordwiseMst-ce frombladeleadingedge,percentchord

Y bladethiclmesscoordinate,percentchord

t maximuma

Subscripts:““d

d design,

2 local

thickness

whenusedwithblades

1 upstresm

APPARATUS,TESTPRWRAM,ANDPROCEDURE

DescriptionofTestEquipment

ThetestapparatususedinthisinvestigationwastheLangley10-inchlow-speedporous-wallcascade(fig.1) describedinreference~ w~ch wasmodifiedby reducingthetest-sectionwidthfrom20 inchesto10 inches.Five-inch-chordbladeswereusedtogiveariaspectratioof2.0. Seven

● bladeswereusedin thecascadeexceptat theMet-air angleof 30°and

4 NACATN4178m

solidityof1.0forwhichonlyfivebladescouldbefittedintothetunnel.Thesidewallsintheentranceto thetestsectioncontaineda flush-type kboundary-layersuctionslot1 chordlengthupstreamfromthebladesectionsbeingtested.Inalltestsa screenofl/2-inchmeshhardwareclothwasinsertedattheentrancetothetestsection.Thisscreenwasinsertedinordertoincreasetheturbulenceleveloftheenteringairinanattempttoreducethelaminarseparationonthetestairfoils.Theadditionof theabovescreenmadetheturbulencelevelcomparabletothatoftheLangley~-inchcascade(refs.1,2,4,and~). Datafromthetwocascadesmaybecompareddirectlywithoutconsiderationoftheeffectsofturbulence.

DescriptionofAirfoils

Thecompressorbladesusedin thisinvestigationwereNACA63-seriesairfoilsof6 percentthickness.Thebladesectionsusedwerethe63-(6.A4K6)06,63-(12A4K6)06,63-(18A4K6)06,and63-(24A4K6)06sections,forwhichtheprofilesareshowninfigure2. Thepartofthedesigna-tionof thesesectionswithinparenthesesfollowsa systemusedexplicitlyforcompressorandturbineprofiles.InthissystemthenumberwithinparenthesesrepresentsthedesignliftcoefficientCZO intenths.ThelettersA toK areidentifiedwiththemeanlinesa . 1.0 to a = O foreachincrementof0.1,andthesubscriptsindicatethefraction(intenths)of theliftcoefficientassociatedtiththeparticularmeanline.Themeanlineandthicknessdistributionofthisfsmd.lyarethessmeas thoseofreference3. ,!TheA4K6meanlineofthepresentseriesavoidsthereflexcurvaturenearthetrailingedgewhichischaracteristicofthea = 0’meanline. Thecoordinatesforthismeanlinefor Czo= 1.0 aregivenintableI. Thecoordinatesforthethicknessdistributionused ●

(NACA63-006airfoil)aregivenintibleIIandthechordwiseloadingdistributionisshowninfigure3. 9

Chokinginbladerowsis determinedbj theminimumpassageorthroatarea. By layingoutlarge-scaledrawingsofthebladepassagesfortheA4K6bladesatdesignangleofattackforvariouscombinationsofinlet-airangle,solidity,andcember,theratioofminimumpassagearea + toinletaxea Al couldbemeasured.Figureh presents~/Al plottedagainstinlet-airangleforsolidltiesof1.0and1.5andcambersof0.6,1.2,1.8,and2.4fortheA4K6bladesection.Inaddition,~/A1 fortheAlobladesection(CZO= 1.2)isgivenforcomparison.Itisappar-entthatshiftingthe~oadingto’theleadingedgehasveryllttleeffectonthearearatiobelowaninletangleof4.0°.Above40°theA4K6sec-tionsincreaseinpassagesreafasterthantheAlosections;hence,theA4K6sectionssreequaltoAlosectionsinarearatioupto40°andmemoreopenathigherinlet-airangles.

NACATN4178

TestProgramandProcedure

Testprogran.- Thecombinationsof inlet-airangle,solidity,andbladesectionforwhichdataarepresentedareshowninthefollowingtable:

p, dega 30 45 60

63-(6~I@6 63-(t$&j06 63-@K$ 06

63-@h~)ti 63-(+2AhK6)06 63-@AkK6)061.0

63-$8A4Kg)06 63-@8A4K+6 *

63-@4A@@ 06 63-~4A@06 *

63-@@+ 63-@@06 63-(6A4K6)06

63-@A@06 63-@4K+6 63-(12A4K6)061.5

63-@A4K6)@ 63-@@c% *

63-@4AhK6)ti 63-&4~K6)06 *

*Stall.occurredbeforedesignangleofattack.

Thetestprogramforthe A4K6bladeswasplannedtoprovidesufficientinformationto satisfyconventionalcompressor-velocitydiagramswhenthesedatasreusedinconjunctionwiththeA1odatapresentedhreference2.

Testprocedure.- Theporous-walltestproceduredescribedinref-erence wasfollowedthroughoutthisinvestigation.Thetestscoveredtheangle-of-attackrangein3° incrmentsfrcmnegativetopositivestallwherestallwasdetezmtiedby a largeincreaseh wakesize(twiceminimum).

Itwasnotpracticaltomaintainthessmeenteringvelocityforallthetestsbecauseofthelsrgevariationh pressureratioacrossthevariouscascsdesmd thechangesinupstresmsxea.~erefore,thetestswererunatnearmsximumoutputofthetunneldrivemotorandtheresultsntReynoldsnumberbasedontheupstreamvelocityandthe~-inchchordVWied frm 297,030to 346,000.TWOcascadec~b~ationswere

6 NACATN 4178.

testedatdesignangleofattackovera rangeofReynoldsnumberfrom160,~0 to385,000toassistinestimatingperformanceatReynolds *nunbersotherthantheusualtestvalue.

Testmeasurements.-Bladepressuredistributions,turning-anglesurveys,andwaketotal-pressurelosswereobtainedby usingthe

—

methodsofreference1. Upstreamconditionsweremeasuredinthe =samemanneras inreference3.

Calculations.- Thecalculativeprocedureiscompletelydescribedinreference1. Briefdefinitionsofwake,lift,anddragcoefficientarerepeatedherein.Thewakecoefficient~1 representsthemomentumdifferencebetweenthewakeandthestreamoutsideofthewake.Allforcesduetopressureandmomentumchangesacrossthebladerowweresunmedto obtaintheresultantblade-forcecoefficient.Theresultantforcecoefficientwasresolvedintocomponentsperpendicularandparalleltothevectormeanvelocityto obtaintheliftcoefficientCzl andthe

dragcoefficientCdljrespectively.Allcoefficientsarebasedonthe .

upstresm

The

dynamicPrf=sme ql.

AccuracyofResults

measuredturning-angleaccuracywaswithinti.5° nearthedesigncondition.Fortestsnearpositiveornegativestalltheaccuracywassomewhatreducedbecauseof increasedwakewidthsintheplaneofanglemeasurement.

“Thebladenormal-forcecoefficientcalculatedfrompressure-rise

andmomentumconsiderationswascomparedwiththenormal-forcecoeffi-cientobtainedby integrationofthepressuredistribution.Sincethese Gvalueswouldbe affectedby errorsinturningangle,surfacepressure,w&e-surveyreadings,ora failureto achievetwodlmensionalityoftheflow,thiscomparisonisa checkoftheoverallacceptabilityofthetests.Theagreementbetweennormal-forcecoefficientsobtainedbytheaforementionedmethodswaswithin5 percent.Theliftcoefficientspre-sentedwereobtainedfrommomentumconsiderations.

PresentationofResults

ThecoordinatesfortheA4K6meanlinearepresentedintableI,andthethiclmess-distributioncoordinatesfortheNACA63-cm6airfoilwithtrailingedgethickened(t/c= 6perient)arepresentedintable11.Theresultsforthevariousbladesectionstestedarepresentedinfig-ures4 to 43,as indexedinthefollowingtable:

.NACATN 4178

FRE9RmTIoIi cmRE30rm

7

“u

.

v

●

NACATN 4178

DISCUSSIONOFRESULTS

OperatingRange

Summariesoftheturningsingle,angle-of-attackrelationshipsforthefourcsmberedbladesect~ons-te&&-aregivenforeachinletsingleandsolidityinfigures25to30. Forcombinationsgivtimoderatepressurerisestherearestraight-linerelationshipsforconsiderableportionsofthecurves.At thehighestpressure-risecombinations(p= 600)thetwo-iMmensionalpressureriseisverynearthestallingpressureriseandthestraight-linerelationshipexistsforonlyasmallportionofthecurve.

.

lhorderto selecttheuppersndlowerlhnitsofangleofattack,Howell’sindexoftwiceminimumdrag(ref.6)wasusedto estimatetheusefuloperatingrangeofthevsrioussectionsatthesolidityendinlet-angleconditionstested.tifigures.31and32a comparisonoftheoperatingrsmgeofthe63-CZ#4K6)06bladesectionswiththatof

‘he65-@@’0 “de s~tiofsofreferenceI indicatesa 2°to 6°

greaterrangeforthe65-CZo~o)10sectionsfortheconditionstested.Thesmalleroperatingrangeofthe63-(cz#4@06 sectionsisattributedto thedifferenceinprofilethiclmess(ref.5). EIadditiontotheeffectofprofilethickness,theloededleadingedgeofthe63-@oA4~)06sectionshasa steeperpressuregradientneartheleadingedgewhichtendsto forma thickboundarylayerontheconvexsurface;consequently,a reductioninoperatingrange3stobe expected. .

vTurningAngle

bladesectionsispresentedto showthedifferent-esindesignsmgle”ofattackandturningangleforthesetwodifferentsections.Zngeneral,thedifferenceisoftheorderof1°forthedesignturningangle.Thedifferenceinthedesignangleofattackis3.9°forthe65-(24A4K6)06blsiiesectionsanddecreaseslinearlywithcsmber.Itcanbe seenthatatthethreeinlet-airangles(atdesignangleofattack)thedifferencebetweentheturninganglesforthetwotypesof loadingissmall.

ReynoldsNumberEffects

As showninfigures35and37thedragcoefficientandturningangleremainalmostconstantabovea Reynoldsnmnberof220,000.

NACATN 4178 9.

Figures34 and 36indicateno significantchangeinthepressuredis-tributionovertherangeofReynoldsnumbertested.*

Figures38and40 showthevsriationof e and cdlat ~ withReynoldsnumberforthe63-(12A4~)06,65-(~Iw)lo, andthe65-(12A10)10bladesectionsat P of600smdks”, a of 1.0and1.5.TheA218bsectionisnotincludedinthelwer met-~Qe fi~ebecausenodatawereavailableforthatcondition.TheA4~ section

hasa lowercriticalReynoldsniunberthantheA@m ortheAlosectionsas indicatedbythelowerdragsndhigherturningugle atthelowerendoftheReynoldsnumberrange.Thisistobe expectedbecauseoftheadversepressuregrsdientbeginningattheleadingedgeoftheA4K6section.

Thevsriationofthelift-dragratiowithReynoldsnumberforthe63-p4%)069 65+%4 ‘0- ‘he65-(w21&0 “de ‘ection‘spresentedinfigures39 ti41 forinletsngl.esof600and45°andsolidifiesof 1.0and1.5. Thelift-dragratiosforthe@l% sectionaregeneralJyhigherthanthevaluesfortheAlosection.Scxnevari-ationoccurredinthecurvesofwakeanddragcoefficientsplottedagainstReynoldsnmnberbecauseofthesuddenchangesinthenatureoftheboundsry-lsyerflowforbothsections;therefore,thedragcoefficientsmdlift-dragratioarenotsufficientlyreliabletousedirectlyinacompressor-performanceanalysis.However,thesevaluesshouldbe ofsomeuseforcomparativepurposes.An evaluationbasedonlift-drag

“(

ratioindicatesthatthe63-CZo\K6)06bladesectionswouldoperate

moreefficientlythanthe65-(cz410)10or65-(CZoA218~10 sectionsin* a compressorupto criticalspeed.It shouldbenoted,however,that

thecriticalspeedoftheseloaded-leading-edgesectionswillbe lowerthsmthatoftheuniformlyloadedortheloaded-trailing-edgesections.

CsrpetPlots

b orderto facilitatetheselectionofbladecsmberanddesignangleofattacktofulfilla designvectordiagram,a csrpetplotofbladecsmberasa functionof inlet-airangle,turningsngle,andsolidityispresentedinfigure43. Designangleofattackmsybeobtainedfromfigure42whichisa csxpetplotofdesignangleofattackasa functionof soliditisndcamber.Thedesi~ sngleofattackwasfoundtobe independentof inlet-airangle.carpetplotsandthemethodof interpolationgiveninreference7.a

.

A completediscussionofof intermediatevaluesis

10 NACATN 4178

SUMMARYOFRESULTS

TheNACA63-(CZOA41%)06cmnpressor-bladesections(whereCzo isthedesignliftcoefficientoftheisolatedairfoil)weredesignedwithrelativelystraighttrailingedges>low IMIXimUIUthickness, andhighaerodynamicloadingintheleading-edgeregion.Comparisonoftheresultsoflow-speedcascadetestsofthesesectionswiththoseofuniformlyloadedorloaded-trailing-edgesectionsindicatesthefollowingcharacteristics:

1.Wekelossesfortheloaded-leading-edgesectionsneardesignangleofattackareslightlylowerthanarethoseforuniformlyloeiiedorloaded-trailing-edgesections.

2.Theangle-of-attackoperatingrangefortheloaded-leading-edgesectionsis2°to 6°lessthantherangefortheuniformlyloadedsections.

3. In contrastwiththeotherbladesections,theloaded-leading-edgesectionsarecapdbleofoperatingefficientlyatthelowerReynoldsnuaibers.

4.Exceptforhighlycamberedbladesathighinletangles,theNACA63-(CZOA4A6)06compressor-bladesectionsarecapableofmoreeffi-cientoperationformoderate-speedsubsoniccompressorsat designangleofattackthanaretheNACA65-(CZOA10)10ortheNACA65-(CZoA#~)10

.

*

“

v

compressor-bladesections.

NACATN 4178.

11

1.Herrig,L.Joseph,Emery,JsmesC.,andErwin,JohnR.: Syst-ticTwo-DimensionalcascadeTestsofNACA65-SeriesCompressorBladesat IOwSpeeds.NACATN3916,1957. (StzpersedesNACARM L51G31.)

2.Erwin,JohnR.,Savage,Melvyn,and13nery,JsmesC.: Two-Dtiensional.Iow-SpeedCascadeinvestigationofNACACompressorBladeSectionslkvinga Systmatic‘lariationinMean-HneLoading.NACATN 3817,1956. (SupersedesNACARML53130b.)

3. Dunavant,JamesC.: Cascadebvestigationofa RelatedSeriesof6-percent-~ckGuide-VaneProfilesandDesignCharts.NACAm 3959,1957- (SupersedesNACARM L5kI02.)

4. Erwin,JohnR.,sndEmery,JsmesC.: EffectofTunnelConfigurationandTestingTechniqueonCascadePerformance.(SupersedesNACATN 2028.)

NACARep.10I6,1%1.

5. Herrig,L.Joseph,Rnery,JamesC.,smdErwin,JohnR.: EffectofSectionThicknesssndTrailing-~geRadiusonthePerformanceofNACA65-seriesCoqressor~ades tiCascadeat tiw@eeds. IIACARM L5zm6,~~1.

6. Howell,A. R.: DesignofAxialCompressors.LecturesontheDevelopmentoftheBritishGasTurbineJetUnitPublishedhWarEhergencyIssueNo.12 ofthebstitutionofMechanical

. Engtieers.A.S.M.E.Reprint,Jan.1947,pp.452-462.

7. Felix,A.Richard:~ of 65-SeriesCcm?pressor-BladeIow-Speedw CascadeDataby UseoftheCarpet-PlottingTechnique.NACATN 3913,

1957. (SupersedesNACARM L54H18a.)

.

.

12 NACATN 4178.

TABLEI.-COOR.DINATESFOR A4K6 MEANLIllE

[Cl.= 1.01

2.0r

100 “

o I

o :0 10020ro

x

o.5

I .252.55.0

10152025

z404550556065

;;80859095100

Y

o.376●7!32

1.3572.2483.5314.4205.0405.4385.7105.&4~.8205.7135.5165.2394.8914.4794.0113.4922.9222.3081.642

●9120

------

0.6237.5034.4100.3131.2110.1483.1023.0659.0359.0104

-.0116-.0308-.0478-.0628-.0761-.0881-.0990-.1090-.1184- .L278-.1387-.1555------

w

.

.

NACATN 4178 13

TABLEII.-

AIEU?OIG

TEICIQiESS-DISTEWJTIONcoommwms FORNACA63-006

WZ21?HTRAILINGEDGETHICKENED(t/c= 6 PERCENT)

[Stationsandordinatesgiveninpercentofchord]

Y:~

.,, ~o 50 100

“x .

x t,

o 01.25 .~l ‘2.5 1.Q575.0 1.462

10 2.01015 2.38620 2.65625 2.84130 2.9$35 3.00040 2.97145 2.87750 2.723

2.51722 2.30165 2.085

1.870E 1.654

1.438g 1.22290 1.00795 .791

100 0

L.E. radius:0.297T. E. radius:0.6

14 UCA‘m4178

Figurel.-PhotographofIangley10-inchcascade. L-87133

.

d

NACATN 4178

u

‘d

—— —. ——

6~6A4i(6)m

—— — —— ——— ——— ——— — —.— —’63-(12A4K@6

——— —63-(18A4K6~6

——— ——— — __ _— —

—.

Figure2.-Bladesectionstestedinthisinvestigation.

NACATN 4178.

w

2.0

1.6

1.2

.8

.4

0

/

‘1%0 /

// \

/ q ‘218b/

\

/

/‘/

/

20 40 60 80 100Percentchord

—.

8

v

Figure3.-ChordwiseloaddistributionoftheisolatedairfoilfortheA4K6,A218b,andAIOmeanlines.

.

.

* . L*

AT~

&,degu .1.0

,6,,deg0-.1.5

Figure1.-Ratioof blade-passagethroatarea to area ofupstreamflowat ~.

I

NACATN4178.

.

3.0CKOnvexsurfoce13Catcovewface

2.0

s

I .0

(d] al =10.8: 8= 14.30(c) a, =7.r ; 8 = Il.&”

3.0-

s

o0 20 40 so 80 100Percent chord

(ei al :i3&, 3 ,17.3?

[ k

~

o 2040 SO SOCQPercentctwd

ff j Q,=&w; $.-23.0”

Figure5.- Blade-surfacepressuredistributionsandsectioncharacteristicsforthecascadecombination~ = 300;a = 1.0;andbladesection

--——--—

63-(6A4K6)ti.

.

.

NACATN 4178 19

32

28

24

20

t?,deg

16

12

a

4

0

/// 20

A=’/

a,,deg

(g) Sectioncharacterlsficej arrowsknwsdesign

Figure5.-Concluded.

angle of attack.

— 08

— 07

— 06

— 05Gv,acd,

— .04

— m

— 02

— .0I

—0

20 NACATN 417!2

.

3.0

2.0

s

I.0

(b) al=13.6”; 8 =20.79°

3.0@anvex surfmeDCcmcavesurface

2.0

s

I.0[1

0(c)al=IG.%Oz23.95? (~)al =19.6”; B=26.95?

3.0

2.0

s

o0 204060 SOl~Percerli Ct-lm’d

(e) a,:22.6:8:29.96?

o 20 40 so so 100Percentdwd

(f) QI =25.%; # =3256?

Figure6.-Blade-surfacepressuredistributionsandsectioncharacteristicsforthecascadecombinationB = 300;u = 1.0;andbladesection

.

v

63-(L2A4~)06.

NACATN 4178 a

40—

36 —

32 —

28 —

24 —

e,deg–

20—

16—

12—

8—

4 —

o—

1.0 t Km0 8 5y

-a

u c1~ /

.9 0 Cdl,P

90A Gw,

/k ~ /

n

..8 $ “/ /

80

?P

.7 / / 7/ /

70d

/ / \

.6 /// 60

c1 / ~/ / \ D

5 / \ 30

/.4 / \ ~

t\ / 40//

/.3 / 1/ / 30

< / LY2 \L / G 20

/ /L

.1 / 10E/

d,.00 4 8 12 16 20 24 28 32°

al,deg(g)Section charocterlstics;arrow sham designangle of attock

— Jo

— 08

— m

— 07

— 08Cw,%

cdl— 05

— 04

— m

— 02

—. 0[

—0

Figure6.- Concluded.

22 NACATN 4178

3.0

2.0 .

,s {

I .q

o(o) al =.17.30;8=27.s?

3.0 b@onvex surfooeDCcmcavesurfwe

2.0 k L

s \ ).~

(c)a,:2331 0:33.3:

3.0

9(2.0

s

I.0

L+ -

ao 20 40 m so ICKI

Percent chwd(e) a,:29.27 8=39.2?

(d) al :26.3” ;8=36.5°

J{

<.

0 20 40 60 SO 100Percentchord

(f) aI 32.3*; 8 =41.2?

Figure7.- Blade-surfacepressuredistributionsandsectioncharacteristicsforthecascadecombination~ = 30°;a = 1.O;andbladesection63-(18A4~J06.

.

.

NACATNkl~ 23

52—

48 —

44 —

40 —

Q,deg —

36 —

32 —

28 —

24 —

20 —

16 —

1,4 -80

0 6’u ‘%1

1.3‘ Io cdl“ m

A Cwl /’ \b ~

1.2 4 70

/ 1&

1.1 / /

T

60

c~ / ~D

1.0 / /u 50

// /

/o

/.9 / 40

&

/

/ /

.8 h } / 30

/~.7 / \\ 20

dA .+. w H L

.6 10

.5 !a f2 16 20 24 28 32 36°

al ,deg(dSectioncharacteristics; arrow shows designangle of attack.

- .08

— 08

— 07

— 06%,a

cdl— 05

— .04

— 03

— 02

— .01

— o


24 NACATN41’78.

.

3.0

2.0

s

[.0

[1

0(0) al =19.3°; 8=32.5?’

3.0OConvexIXOncave

2.0 c)

s

I.0

03(c) al =25.37 8 :39.4?

3.0

2.0t

s

I .0

No 20 40 m w m

Iaurfgce

1

T

~

4

LVo 204060601&

Percentctmrd(d) al =28.5”;8=42.3”

Percent chord(e) al :31.59;6’=45.5?

Figure8.-.Blade-surfacepressureforthecascadecombination~63-(24A4K6)06.

distributionsandsection= 300;u = 1.0;andblade

—

—

characterstiessection

.

.

Y NACATN 4178 25.

56

52

48

$, deg

44

40

.36

*

32

28

— 1.5 I Itoo

o e—

❑ Cli

— 1.4-~ cdl 90A Gwl

/—b ~

— 1.3 /

– cl

— f.2 /

—. 1.1T 60

—

— [.0 50

—

— .9 40

—

— .8 ! 3016 20 24 28 32

— 07

—

— .06

— .05Cw,8

cdl— .04

— .03

— 02

—.01

—c)

~t ,deg(f) Sectioncha~acterlstics;arrow showsdesignangleof attack.


.

—-

26.

.

3.0

2.0 .

,s

I .0

CL1(0) a, = 2.8°; 8:6.9°. (b) al:5.8°; 8: 9.8S.

dAA-1-uP=&ki I-$--d. l I I 1%

a‘m E!rElm(c)a,:8.8°;@.1~.9? (d) a, =11.8°; 8: MXf.

3.0

2.0

s \

I .0

r

o0 20 40 60 so Icxl

Percenfchofd(e) al :14.w; 8:19.00,

[1

0 20 40 60 SO 100Percent chord

(f) a, =17.s0; e :22.m

.

.

.

Figure9.- Blade-surfacepressuredistributionsandsectioncharacteristicsforthecascadeccmbhation~ = no; u = 1.5;andbladesection63-(6A4K6)06.

.

.20 —

24 —

20 —

16 —

ll,deg –

12 —

8 —

4 —

o—

.7

0

❑

6 — - 0

A

h

.5

.4 .

(+

.3

.2

.1

,0-4

-r 70.9

qcdl P

- 60Cw,

~.-

n 50

/

E

. / 40

4.9 ~

$

D

//

- 30

F r } ;/

20

/7/

/%.

/ 10

t4 8 12 16 20 24

—

a, ,deg

[g) %ction characteristics} orrow sham design angle of attack..

I?lgure9.-Concluded.

107

06

:

02

,01

0

28 NACATN4178

3.0

2.0I

,s

I.0

d(a) a,=n.w;9=19.7:.

3.0CKmfivexOCancave

2.0

s

CrJ(C) al =16.8°; 8=26.1?

Perced dud(e) a,=22.8:; 8=32.0?

3’+

u(b) al =13.6°; 6 =22.7?

surfacesurface

l-c-cJ-n+

L1

(d) a, =19.&; 8=29.1?

\b.

t0204060 S0100

Percent ctxml(f) atZ5.8”; 8 =35.1?

.

.

Figure10.- Blade~surfacepressuredistributionsandsectioncharacteristicsforthecascadecomb~.nationP = 30°;cf= 1.5;andbladesection63-(L2A4K6)06.

NACATN 4178 29

44 — 1-o

40 — .9

36 — .8

32 — .7

e,deg— c+

28 — .6

24 — .5

20 — .4

16 — .3

12 — .2

0 e❑ %1

–o ‘d,

A Cwl

h

4 8 12 16 20 24 28a,,deg

—08

— 07

— 06

— 05Cw,

— %cdl

— .04

— 03

— 02

— .0I

— o

(g) Sectioncharacteristics; arrow sfmwe design angle of attack.


30 NACATN 4178.

3.0

2.0

s[

o(0) a, :18.8°; 6’: 32.7?

c1

(b) “Ul =21.8”;6.35.4?

3.0CXOnvexsurfocefJCmOaveeurfme

2.0

s

I .0

r[

o(c) a, =24.S; 8 =38.2? (d) at =27.8”; 8=4J.2?

3.0 ,

2.0 (

s \

1.0 k

I 4 ~ - ?

Cmo 20 40 W 80 100

Percentchcmd(e) al:30.f3*;8 =44,2:

?

l-d * -

20 40 60 00 00Percentchord

(f ) al :33.y ;8 :47,3*

Figure11.- Blatle-s”urfacepressuredistributionsandsectioncharacter-isticsforthecascadecombinationp = 300;G = 1.5;andbladesec-

.

.

tion63-(MA4~)06.

.

.

4

52

48

44

8,deg

40

36

32

28

– 1.0 I I 700 e

—n q

o cd,– ,9—A P \

(3WI 60

L/— —h ~ ,

– .8 / / / 50

– cl~/

/ D

– .7 P/ 40

s\

\ /r~

/

– .6 / 30

— //

t

– .5 / 20

c– .4,2 t

16 20 24 28 323610

al, deg

(g) Section characteristics; arrow show design angle of attack.

Figureil.- Concluded.

— 06

— 05

— .04

Cw,— %

cdl— m

— 02

—. 01

—0

.

3.0

2.0\

.s7

I .0 n b

o(o) a,=25.3”; @”:355?

3.0 IOConvexnurfwemave wrface

k

s L

I .0

A

Cu(c) a, =3150;8=49.5? o 20 40 60 80 100

3.0

&

2.0 k.

s Y ~

1.0

0 204060 SOl~

!+rcent chord(d) % W.8”; @ =52.&

.

.

Percent clmrd(e) al=37.8”;9 :55.s!

Figure12.- Blade-surfacepressuredistributionsandsectioncharacter-isticsforthecascadecombinationB = 30°;a = 1.5;andbladesection63-(24A4~j06.

.

.

.

NACATN klm 33

60 —

56 —

52 —

48 —

e,deg—

44 —

40 —

36 —

32 —

(f) Secti

1.2I

70

0 e

u %[1.1—0 cdl 60

A Cw,w

L ~

1.0 / 50

/ ,

.9‘ # 40

cl &D

.8 ‘s 30

/ \

.7‘ d 20

.6 d10

d\

%“4 28 32 36 48al ,deg

on characteristics;arrow showsdesignangle of a

— 07

— 06

— .05

— .04Cw,

— %cdl

— .03

— 02

— .01

do

ttack.


34 NACATN 4178

3.0

2.0

,s

I .0

CW(a) a,=l.~ ; 8= 3.5?

3.0 *@OnvexOCcmcave

s

I .0

#(c) al =7.8°; 8 =99?

3.0

2.0

s[1

I .0

ti~

o0 20 40 60 so I@

Percent chard(e) al :13~0; @❑15.6?

(b] a, =4.6° ; 6’=7.~

surfcce5urface

[

(d) al =!0.S”; 8 =12.9?

I

o 20 40 60 80 100—

Percent chard(f) al=17JY;9=18.0?

Figure13.- Blade-surfacepressuredistributionsandsectioncharacter-isticsforthecascadecombinationP = 450;a = 1.0;andbladesec-tion63-(6A4K6)06.

.

NACATN 4178.

●

28—

24 “

20—

16—

e,deg—

12—

8 —

4 —

o—

al,deg

(g) Section characteristics; arrow showsdesign angle of attack.

107

— 06

— 05

— 04CW1

. %cdl

— A3

— 02

— .01

— o


36 NACATN 4178.

3.0 .OCOnvexUConcave

2.0

s ,

1.0

a(c) al =13.80;6’=19.9”.

3.0

I

s c1\ \

1.0 \

J+=f

o 10 20 40 60 so m

Percent clwrd(e) al=19.50; 9s25.0”

(b) al = 11S’; 6: 17N.

,surfocesurface

1

\

[1

(d] a, =16f1°; (?=22.7”.

Percent chord(f) a,=226: @=27.3°

Figure14.- Blade-surfacepressuredistributionsandsectioncharacter-isticsforthecascadecombination~ = 450;a = 1.0;andbladesec-

—

tio~63-(L2A4K6)06.

.

NACATN 4178 37.

●

36 r

32 —

28 —

24 —

20 —

8, deg—

[6 —

12 —

8 —

4 —

o—

.8 1 900 e❑ Cll

0 Cdl.8

/ 60A Cw,

k ~

.7 / / ‘\ 70

d/’

.6

.5

C*

:/ D

.4 9

lb’ 1

40

.3 /

/ AI

30

d i/$

.2 u/y

20

L

J~ ~

/L b—\ / 4 10

~ik

.OO 4 8 [2 16 20 24 28°Q,, deg

(g) Section characterletics; arrow shows design angle of attack.


— .@

— C)8

— 07

— 06

— 05Cw,

— %cdl

— .04

— m

— 02

— .01

— o

NACATN 4178.

.

3.0

2.0

,s/

2

I .0

0(a) at ..15.8°; o =,24.7.

t1

(b) a, =18.5”; 8 =.27~.

3.0 OCorwextwrfawuCancavesurface

2.0 h.

s (

I .0

[

o d(c) al :2t25~ o =295”. M) a, =23.3°; @=32.1°.

3.0

2.0

s

I .0

20 40 so 60 1~Percentclmd

(e) a, =26.6”; 8 =343°.

\

-(

0204060 S0100Pwcertclwrd

(f) al 29.&, 6 = 36.0°

Figure15.- Blade-surfacepressuredistributionsandsectioncharacteristicsforthecascadecombinationp =450; a = 1.0;andbladesection63-(18A4K6)06.

---

.

.

NACATN4178 39

44 —

40 —

36 —

e,defg—

32 —

28 —

24 —

20 L

1.2I I 900 8 \❑ Czl

1.1—0 cdl 80A Cwl

A k1.0 70

c~ ~D

.9 60

A\ A

c1.8 50

/

.7 ~ u v u “ 40

(+

.612 16 20 24 28 Sz30

al ,deg

— .06

— .05

— .04Cw,a

Cdl— m

— 02

— .01

—0

(g) Sectioncharacteristics j arrow showsdesignangleof attack


40 NACA‘m 41’@.

.

3.0

2.0 k.

,s (

I .0

0(a) a, =19&; 9=30.9.

---

1 I I I (J%-ivexsurfaceOccacove surfcce I I I I

f31i31mI

* I I I I I I I I I I(c) al =25.8”;0 =37.0”. $ 20 40 60 80 100

3.0

Y (

2.0

s

I .0

00 20 40 60 80 ICQ

Percent ch+xd(d) al :28.8”; 8 =3S.8”. a

.-

Perceot chard(e) a! =31S0; 6’=42.0°.

FigureI.6.- Blade-surfacepressuredistributionsandsectioncharacter-isticsforthecascadecombination~ = 450;a = 1.0;andbladesection

.—

63-(24A4K6]06.

+

.

Y NACATN 4178

44

40

e,dea.

36

32

28

24

—

—

—

—

—

—

—

—

—

1.2 I I 800 e

❑ c1[

1.1—Q Cd, 70A Gw,

c1 —b ~D

1.0

.9

.0 40

.7 1! A3016 20 24 28 32

al ,deg(f) Sectioncharacteristics;arrow shows


— .05

— .04Cw,

_ %cdl

— .03

— 02

— ,01

— o

designangleof attack.

42 NACATN 4178

3.0

,s

I .0

d(a) a, :5.30; 8=8.20.’ (b) al =8.8? ; 9=11.6°.

I I -A I I I I ~1 I I tI.0 I I1 111 I 1 t-

~L_l_LLu(c)al=11.80;O=[4.70. (d)al=14.6°;~=18.4°.

3.0

2.0

s

!.0

o0 20 40 60 SC 103

Percent chord(e) a, =17.8”;8 =Zm”

[I >\

l-d P--d

h0 20 40 60 60 ICKI

Percent ctwd(f) a,=20s”;8.23.3”.

Figure17. - Blade-surfacepressuredistributionsandsectioncharacteristicsforthecascadecmnbinationp = k50;a = 1.5;andbladesection63-(6A41%)M.

.

.

28

24

20[

16

(?,deg

12

8

4

0/

al ,deg

(9) Section chorasterlstlcs} arrow shows design angle of attack.

Figure17.-Concluded.

i

08

0!5

04

cwl8

Cdl

1m

02

.01

44 NACATN 4178

3.0

2.0

s k

+ -

L

~ &

%(a) al=lo.lo; 8=171°.

3.0@arrvexUCarcave

2.0

s

I .0

N(c) a, =17.6°; 8z25.9”.

3.0

2.0

s

I .0

00 20 40 60 60 m

Percent chard(e) Cf,=238*; 0=31.5°.

)

7

H--l-MLr

@(b) al=14.W, 8=22.5°.

eurfacesurface

r1

(d) a,+0.6°; O+R6”.

(

o 20 40 60 60 100Percentctwd

(f) a,=296°; 6=36.7”.

Figure18.- Blade-surfacepressuredistributionsandsectioncharacteristicsforthecascadecombination~ = 45°;u = 1.5;andbladesection63-(~4K6)06.

.

.

t ,

40 —

36 —

32 —

28—

E4—

8,* .

20—

Ie—

If!—

6 —

4 —

Lo — m

s — m

B — 07

.7 — 06

.6 — n5

G1 y

cd,5 — 04

.4 — m

3 — C2

.2 — .01

.I — o

al,deg

(d%efkma!mmcferletlcalarrowah @signrinrjbofaitack,

Figure18.-Concluded, &-

46 NACATN 4178

3.0

2.0

,sf 1

I .Ci

o(a) a, =lE&; 8=30.4”.

I Y

1(b) ‘a, =21.6°;13:33.7”.

3.0, ,[ 1 i I firm””.” ..,.?-. I I I I 1

H--H-R?F+H--H

(C) al :24.87 () =36.5°.

3.0

s {

I .0 k

20 40 60 SO 1~Percent clmrd

(e) al =m.5”; .9 =425:

20 40 so so lmPercent ch~d

(f ) a,:33.s”;Q:457”

Figure19.- Bkde-surfacepressuredistributionsandsectioncharacteristicsforthecascadecombinationP = 45°; ~ .= 1.5; andbladesection63-(18A4K6)06.

.

.

.-

t , ●

52 — .9Io e

n %1

48 — .8—o cdl

A Gwl

h $

44 — .7

/ ,+ ~ “ / ‘

40 — .6 /

El, deg — c1? ( /

36 — .5/

\

\\

32 — ,4/ k Y

/ti

/ o \

> -jjI c28 — ,3

/v

Yu

Z4– “z 2 16 20 !4 26 32

a,, tleg

(g) %dion characterktics~ arrow shows design ongle of attack.


~

07

06

— (35

— 04h,

a

‘d,— 03

— 02

— .01

.

48 NACATN 4178

3.0

2.0

s

I .0

[30

(o) Cll z24.&; 8 =3S.&.

3.0@htvexDCcmcove

2.0 Jm-

S\ ~

I.0Y \

eurfm! surface

?

UII I I 1(c) al =31.1”;8 :46E”.

3.0

2.0 t

s

1.0 \

o 204060 S0103Percenl chmd

(e) al =56EP;0 .521Y

(d) a, =3?tso;0:49.4”.

t

c

o 20 40 60 SO 100Percent clmd

(f). al =39&; @=53.2°.

4

.

Figure20.- Blade-surfacepressuredistributionsandsectioncharacteristicsforthecascadecombination~ =450; a =-”1.5;andbladesection,63-f24A4K6~06.

.

-4I

*

60 v

56 —

52 —

B,deg –

48 —

44 —

40 ‘

36 —

I , * . I

1.1‘ I I -600 0

k ou %[

cd,1.0—~/& - Y

/ 50A Cwl

\L ~ (

/

.9” A 40

cl~ / ~/ D

.8 30{

.7 20—

[

.6 / 10

/i\

.520 24 28 32 36 40 44°

al,deg

@ %ctiar) characteristics; arrow shows design angle of attack.

Figure20. - Concluded.

— 06

— 05

— 04

Cw,— %

cdl

— 03

— 02

—, 01

—o

I

50 NACATN 4178

3.0

2.0

,s

[10

(a) a,: ..7° ; 8 =l.OO. (b) a, =20” ; 8=3.6”.

..-OCaivexUCancaw

s

1.Q

(C) U, :4.8° ; @=6.80.

w“rface! Surfme

(d) a, :7.&;8.9,6”,

3.0

2.0

s

1.0c1

00 20 40 Sa so m

Percent chord(e) a,=tw; 9=H.W.

[

o 20 40 60 W 103Percent ctwd

(f) a, :13.80; 6 =13,50.

Figure21.- Blade-surfacepressuredistributionsandsectioncharacteristics‘forthecascade63-(6A4~)06.

ccmibinationP = 600;u = 1.0;andbladesection,

.

NACATN 4178 51

28 ‘

24 —

20—

16—

6,deg —

12—

8 —

4 -

o—

.6tt

o

A ‘-’W1 I 1/ I hlAllllt--t’-M--t-

(g) Section characteristics; arrow showsdesignangleofattack.

— 07

— 06

— S35

— .04Cw,8cdl

— m

— 02

—.0[

- 0

Figure21. - Concluded.

NACATN 4178

2.0 T

.s

I.0

(o) a, =’3.80; e :10.7*.E

(b) Ul =880, 8=)36°.

(C) II, =l[SO; ~=16.4°.

3.0

[ i

I .0 c

o 20 40 60 80 100Percentckfd

(e) ~1=17.8*; 6ct9.&.

3.0 * *OCOnvexsurfm.a❑ Mmve surface

2.0

s\ \

I.0 [i Y

ailo 204060601m

Percent chcfd(d) a, s14.6?;e =18.6°.

s

.—

Figure22.- Blade-surfacepressuredistributionsandsectioncharacteristicsforthecascadecombination~ = 600;a = 1.0;andbladesectfon63-(12A4K6)ti.

.

.

53

.

.

.

48—

44 —

40 —

36“

32—

Q,de~—

28—

24—

20—

16“

12—

8—

1.4I I

100

0 .6❑ Czl

c

1.3—~ cdl 90

1.2 I ‘80

1.1/

70

/

1.0 I/ 60

cl &

!D

.9 50

/

.8 II/

40

.7 IL~ / 30

/

I I Id I l/H20

{10

I I I #’l IT.4

a, ,deg

— Jo

— ..09

— f)8

— f)?

— %36Cw,

— %cdl

— 05

— .04

— m

— 02.

— .0[

—0

(f) Section characteristics; arrow showsdesign angle of attack.


54

3.0

2.0

,s

1.0

n 1(0) C$=4,P.;8=6.5°.

3.0CyAVexgcalcova

2.0

s

all(c) al =.10.018=!1.8°.

s

3.e

m

Y

o0 20 40 60 60 103

Percentctmd(e) al=16.W; 8=17.0°.

-.

NACATN 4178 . ,“*. ..

.

airfoceWrfmx

1

(d) a, :12.eO;8:14.20.

Percent ‘ctwd[f) Q! =18.8°; 8 =16.2°

Figure23.- Blade-surfacepressure.distributionsandsectioncharacteristicsforthecascadecmnbinationp = 600;u = 1.5; andbladesection63-(6A4~]06.

.

HACATN 4178+

55

.

24 —

20 —

16 —

e,deg—

12 —

0 —

4 —

o—

.6 I 600 8n c1[

~ .0 %,. 50A Cwl

A ~

.4 40

C+ ~f /- D

.3 / J J-i “30

/

.2 - / 20

.1 L 10

/

.00 4 a !2 16 28

al, deg

(g) Sectioncharacteristics; arrow shows design angle of attack.

— 06

— 05

— .04Cw,8cdl

— 03

— 02

— .01

—0

Figure23.-Concluded.

NACATN 417’8

3.0

.s

i .0

(o) a,=8.3* ; 8= 11.zP. (b) al :lO&; 8=16.9”.3.0 (JCanVox surfoce

❑Ccacave eurface

2.0.

s

%(c) at :13.80; 9 :i9w (d) a, ..16.8°; ~ :23.rY.

3.0

2.0

s

o0 20 40 60 6Cr 100

Percent chard(e) al =20.1°; @=26.3°.

(

c

L

o 20 40 60 SO lCOPerceni cbd

(f} a,=23.l”; ~ :265”.

Figure24.- Blade-surfacepressuredistributionsandsectioncharacteristicsforthecascadecombination~ = 600;a = 1.5;andbladesection63-(12A4~)06.

.

.

.

.

z NACATN 4178 57.

.

32 —

28 ‘

24 —

8,deg—

20 —

16 —

12 —

8—

.

OH.6 ---

n q–0 cd,-

A Cw,.5–

b ~

.4

cl

.2 /

.1

.08 12 16 20 24°

al ,deg

— .06

— .05

—. 04Cw,8

%1—. 03

—0 2

— .0I

—0

(g) Sectioncharacteristics;arrow showsdesignangleof attack.


e

48 —

44

* /

O 63-(6A4K6)06

36 u63-(12A4K#)6063-( 16A4K6)06A63.(2LIAAK6)06

d/ /0

32 //

F

J7

28 J/

‘,deg //

24 L /-

/

20 / P

//-

I6 ! /

c /

/ /

12

8

.

4

I ! I I 1

I00

1 I I I I 1 1 1 ! , , , I , 14 0 12 16 20 24 28 32 36

al ,deg

Figure~.- Summariesoftheturningangle,angle-of-attackrelationshipsforthefourcamberedbladesectionstested;p = 30°;a = 1.0. Short “--baracrosscurveis designangleof attack.

-“

.

.

.

.

.

NACATN 4178 59

56’

52

46/

44 0 63-(6A4K61a6 /“

u 63-!12A4K6106O&(18A4K6]06 /A 63-(24A4K~06

40 /

/

36 /

/

32 / r

19,&gc~

/28 /

/24 /

P/

/20 /

u

16

12

8

fi

o0 4 8 12 16 20 24 28 32 36 40

al ,deg

Figure26.- Summriesoftheturningangle,angle-of-attackrelationshipforthefourcsmberedbladesectionstested;p = 30°;o = 1.5. Shortbaracrosscurveisdesignangleofattack.

s

60 NACATN4178●

44

A

40 / ‘

/

36 ?A

P

32 No 63-(6A4K6)06❑ 63-(12A4K6)06 ,2‘

‘O 63-(18A4K6106A 63424A4K6)c6

9

28

/P

/ y/

24 / ““

8,deg d

20

16

12

.

0

4 L

00 4 8 12 16 20 24 28 32 36

al ,deg

Figure27.- Summariesoftheturningangle,angle-of-attackrelationshipsforthefourcamberedbladesectionstested;~ = 45°;a = 1.0. Shortbaracrosscurveisdesignangleofattack,

.

.

.

NACATN4178 61●

.

.

.

.

56-

52

46

44

0 63-16A41Q06~ 63-U2A4K61C6 /

40 063-(18-44K6)06 /A

A63-(24A4K6]OS

36 P

32

,~,deg

28/

24 ~

(

20

//

fo/

16 /

12 /

//F

0 d.

4

00 4 8 12 16 20 24 28 32 36 40

Figureforbar

a, ,deg

28.- Summariesoftheturningangle,angle-of-attackrelations~psthefourcamberedbladesectionstested;,~= 45°;CT= 1.5. Shortacrosscurveisdesi~angleofattack.‘

-.

.-

20

16/

12 / F

0 ,degc

/

8O 63-(6A4K6)06

4

0 .~-4 0.4 8 12 16 20

a, ,deg

Figure29.- Suwmrles of thet.urnlngE@Le& a.ngl.e-of-attackrelationshipsfor two camberedblade sections; ~ = 60 ; u = 1.0. Short baracrossconeis deeiga angle of attack.

, .

NACATN 4178 63.

.

.

Fi

28r

/~ -Cl

24-

/

20 /

16

e, deg /

12-b

8 .

I

4-

00 4 8 [2 16 20 24

al, deg

.gurew.- Summariesoftheturningangle,angle-of-attackrelationshipsfortwocamberedbladesections;@ = 600;u = 1.5. Shortbar.acrosscurveisdesignangleofattack.

64 NACATN 4178

u

30C20

:1:26 A18

1h —A4K6\

<>’ --–- Alo Ref.1.\~>

22\

\\\.\

\ ‘\Y \ Y>--\

\ \ --18 /.

\[Y

14

10 <)

“m 30 40 50 60 i’~l,deg

Figure31.- Variationofwith“inlet-air

theestimatedoperatingangle-of-attackrangeangleforseveralcambers;u = 1.0.

.

.

Jy.

.

.-

.

3U%0

/ I\ ‘\\ 04

() \ 5626 \ \% \\ 012\ L

\\ A 18\\\ \ LL & 24\\\ \ A4K6

22 .’ ~ \At.+\

[I \~ \\ . \18 \ \\ \ K\\

\ \\ \

!14

\\

\\

10 \\

\\1,

:07

30 40 50 60 o

Figure32.- Variationofwithinlet-air

theestimatedoperatingangle-of-attackrangeanglefor severalcambers;u = 1.5.

.

.

66 NACATN 4178.

aA4K6– aAlo

QA4K6– aAlo

2

vo

[ \

4 -2

lll1147f1’ 111 i

8A4K6- $~,o

2

t

o9 .8 1.2 1.6 2.0 2.4

QA4K6- QA,O

.

.

Figure33.- Differenceindesigna and Elforthe63-(CZOA4.K6)06and

65-(CzoAIO)l~bladesections.

.

NACATN 4178 67

3.0 (

2.0

s1

f.0 .[1 x

o(0) R ❑159,000. (b)R .220,000.

3“0FFFFE’FFFFs r \

I.0

c

o(c)R .272,000. (d) R =313,000.

k%kllll w3.0

2.0

s

I .0

[

o0 20 40 m so 100

Percent CIWrd(e) R ~346,000.

\ \

Y[1

0 20 40 so so 100Percent chord

(f) R =m5,000.

Figure34.- Blade-surfacepressuredistrib@ionsatvariousReynoldsnum-bersforthecascadecombinationj3= 45°;IS= 1.5;andbladesection63-(M4~)06;a =17.8°.

32

O,deg

28

24

{f!

c

o 8

A Cw,

\

L )n n

u u Q

I I I I I I I I I I I I

22 26 30 34 38

02

Cw,%

cd,01

0? XI04

Figure 35.- VariatIonof section characteristics of the 63-(12Ak~)Ckprofiles with Reynol& num-

ber; ~ = k~”j a = l.sj a = 17.8.

. ,, ,, 1 1

● ✎

NACATN 4178 69

3.0

2.0

s L

I .0? ~

~ l-l-l-f ~

o(a) R =159,000. (b)R .220,000.

3.0@Onvex eurfatx❑Ccmcavesurface

2.0

s

I.0

t+1(c~R =272,000.

3.0

s

ao 2040 SO SOIW

Percent tid(e) R =346,000.

(d)R..Sls,ooo-

0 20 40 60 00 100Percent chcrd

(f) R =365,000.

Figure36.-.Blade-surfacepressuredistributionsatvariousReynoldsnum-bersforthecascademmbination p = 600;a = 1.O;andbladesection63-(12A4K6)06;a = 14.0.

-ao

28 I 1 030 eo cdl

A Cwl24 ‘ 02

L\O,cleg

Cwl

< \8

A& A cdlAu A20 ~ O--— _J& .

v

a/\

0.01

c bx> u w u w

n

1612 16 20 24 28 32 36 40 4$x 104

R

Figure 37. - variation of sectionc~acteristics of the 63-(1.2A4~)06her;p = 600; a = 1.0; u = 14°.

, .

profiles with Reynolds num-

. .

I ‘ .06

0 — -e 7 * i-l n n f .05—

()----/ .

./J ~./

// 0 O-emax/

-1 ,N❑ cdl

/ – .04(Y — 63-(12A41(6]06

[/ --–- 6542AIO)10 Ref.I

‘-—65-(12A218#() Ref. 2

g -2,\ ,/

‘.03cd,EmA

\o.02

I .-.

~ k-- --.

-4 ~— — — — — - –— + — — — !7E “-—— — .y .01

-5 016 20 24 20 32 36 40 44 48

R52X 104

Figure S.- Variation of e - e- alla cdl withReynolde number at ad; p = 60°; u = 1.0.

!2

80

0 63-(12 A4Kfj)06o /

A c 65-(12A+Q)I0 Ref. I

70 . ----/ ~ 65-(12 A211#Q Ref. 2

/ 5 ~N /

60 / ‘ / &// ~

r// /

-Lm 2[ // //~ /-6

40- /

30///

20 /

Io16 20 24 28 32 36 w 44 48 52X104

R

Figure 39.- Variat.ionof L/D with Reynolds number at ad; ~ = 60°; u = 1.0.

-aN

, . # .s

)-.

# , v * ● 42

I06

0 - - u . mu 115

Y ‘-’ “-o- -y//

/-1Y- .04

oe-~❑ cdl

— @W.A4K~ d

-2---- 6$-(1~o)lonef.1

x 03

zm

cdlCA

-3. 1)2--

Y L.

--,

1-❑ -—- -u. . .

-4 n n -u-. n-m .01—-

-5,620 24 28 ~ 32

036 40 44XI04

Figure h.O. - VUiatiOn Or e - e= and Cq with Reynolds number at ad; ~ = h5°j U = 1.5.

-.

-b

.

-1-r=

40 44x ,04

~

Figure kl.- Variatlon of Lb wltihReynolds number at ad; ~ . h~o; u . 1.5. >a

5

.-!

1

Figure b2.- %wl.ga angle-of-attackCW~~H::t:O&r theNACA 63-( CZ#4K5)06.

compressor-blade

,

-1U

I

aw~ Figure 43.-Iksigo turning-anglecarpst plot for the N/KM 63-(CzoA4~)06cmpressor-blade sections.+<.

1

. .

i.

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NATIONALADVISORYCOMMITTEE FORAERONAUTICS/67531/metadc... · cm nationaladvisorycommittee foraeronautics technical note 4178 low-speedcascadeinvestigationofcompressorblades havingloadedleadinge~es