chapter 4 laminar boundary layer inviscid ...syahruls/resources/mkmm-1313/chapter-04/...chapter 4...
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CHAPTER4LAMINARBOUNDARYLAYERINVISCIDFLOWPASTWEDGESANDCORNERSFALKNER-SKANSOLUTIONInfluiddynamics,theFalkner–Skanboundarylayer(namedafterV.M.FalknerandSylviaW.Skan)describesthesteadytwo-dimensionallaminarboundarylayerthatformsonawedge,i.e.flowsinwhichtheplateisnotparalleltotheflow.ItisageneralizationoftheBlasiusboundarylayer.FalknerandSkan(1931)foundthatsimilaritywasachievedbythevariable𝜂 = 𝐶𝑦𝑥^,whichisconsistentwithapower-lawfreestreamvelocitydistribution.
𝑈 𝑥 = 𝐾𝑥a
𝑚 = 2𝑎 + 1Theexponent𝑚maybetermedtheFalkner-Skanpower-lawparameter.Theconstant𝐶mustmake𝜂dimensionlessbutisotherwisearbitrary.Thebestchoiceis𝐶g = h ija
gk,whichisconsistentwithitslimitingcasefor𝑚 = 0,theBlasius
variable.
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Thus;
𝜂 = 𝑦𝑚 + 12
𝑈 𝑥𝜐𝑥
= 𝑦𝑚 + 12
𝑈𝜐𝑥
Substitutingthisparticular𝐶intoEq.4-67,givesthemostcommonformoftheFalkner-Skanequationforsimilarflows:
𝑓ttt + 𝑓𝑓tt + 𝛽 1 − 𝑓tg = 0where
𝛽 =2𝑚1 +𝑚
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EXAMPLEEstimatethevariationofsurfacevelocityalongthewallifangleofwedgeis10°.
Knownthat:𝑈 𝑥 = 𝐾𝑥aand𝑚 = 2𝑎 + 1yzg= 10°,sothat𝛽 = i
{
𝛽 = ga
ija= i
{,sothat𝑚 = i
i|
Velocityprofileis𝑈 𝑥 = 𝐾𝑥
}}~
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𝛽 𝑚 Descriptionofflow
−2 ≤ 𝛽 ≤ 0 −12≤ 𝑚 ≤ 0 Flowaroundanexpansioncornerofturningangleyz
g
𝛽 = 0 𝑚 = 0 Theflatplate
0 ≤ 𝛽 ≤ +2 0 ≤ 𝑚 ≤ ∞ Flowagainstawedgeofhalfangleyzg
𝛽 = 1 𝑚 = 1 Theplanestagnationpoint(180°wedge)
𝛽 = +4 𝑚 = −2 Doubletflownearaplanewall
𝛽 = +5 𝑚 = −53 Doubleflowneara90°corner
𝛽 = +∞ 𝑚 = −1 Flowtowardapointsink
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THEPLANELAMINARJETFLOWConsideraplanejetemergingintoastillambientfluidfromaslotat𝑥 = 0,asshownbelow:
Inthissituation,theconservationofmomentumwasapplied.
Momentumflow,𝑚𝑉 = 𝜌 𝑉 ∙ 𝑛 𝐴𝑉 = 𝜌𝑉�𝐴𝑉
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Themomentumfluxisdefinedasthemomentumflowperunitarea.Wecouldsimplifyitas:
Momentumflux,𝐽 = 𝜌 𝑢gj�
��𝑑𝑦 =
169𝜌 𝜐i/g 𝑎�
𝑎 = 𝑐𝑜𝑛𝑠𝑡𝑎𝑛𝑡
Themaximumvelocitycanbeconcludedas:
𝑢a^� = 0.4543𝐽g
𝜌𝜇𝑥
i/�
Wemaydefinethewidthofthejetastwicethedistance𝑦where𝑢 = 0.01𝑢a^�:
𝑊𝑖𝑑𝑡ℎ = 2𝑦 i% = 𝑏 = 21.8𝑥g𝜇g
𝐽𝜌
i/�
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Themassflowrateacrossanyverticalplaneisgivenby:
𝑚 = 𝜌 𝑢j�
��𝑑𝑦 = 36𝐽𝜌𝜇𝑥 i/� = 3.302 𝐽𝜌𝜇𝑥 i/�
whichisseentoincreasewith𝑥i/�asthejetentrainsambientfluidbydraggingitalong.Thisresultiscorrectatlarge𝑥butimpliesfalselythat𝑚 = 0at𝑥 = 0,whichistheslotwherethejetissues.ThereasonisthattheboundarylayerapproximationsfailiftheReynoldsnumberissmall,andtheappropriateReynoldsnumberhereis:
𝑅𝑒 =𝑚𝜇
Thus,thesolutionisinvalidforsmallvaluesofReynoldsnumberof:
𝑅𝑒 =𝐽𝜌𝑥𝜇g
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EFFECTOFPRESSUREGRADIENTSEPARATIONANDFLOWOVERCURVEDSURFACESAllsolidobjectstravelingthroughafluid(oralternativelyastationaryobjectexposedtoamovingfluid)acquireaboundarylayeroffluidaroundthemwhereviscousforcesoccurinthelayeroffluidclose to the solid surface. Boundary layers can be either laminar or turbulent. A reasonableassessmentofwhethertheboundarylayerwillbelaminarorturbulentcanbemadebycalculatingtheReynoldsnumberofthelocalflowconditions.Flowseparationoccurswhentheboundarylayertravelsfarenoughagainstanadversepressuregradientthatthespeedoftheboundarylayerrelativetotheobjectfallsalmosttozero.Thefluidflowbecomesdetachedfromthesurfaceoftheobject,andinsteadtakestheformsofeddiesandvortices.Boundarylayerseparationisthedetachmentofaboundarylayerfromthesurfaceintoabroaderwake.Boundarylayerseparationoccurswhentheportionoftheboundarylayerclosesttothewallorleadingedgereversesinflowdirection.Theseparationpointisdefinedasthepointbetweentheforwardandbackward flow,where theshear stress is zero.Theoverallboundary layer initiallythickenssuddenlyattheseparationpointandisthenforcedoffthesurfacebythereversedflowatitsbottom.
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Wehavesofarconsideredflowinwhichthepressureoutsidetheboundarylayerisconstant. If,however, thepressure varies in thedirectionof flow, thebehaviourof the fluidmaybe greatlyaffected.Let us consider flow over a curved surface as illustrated below. The radius of curvature iseverywherelargecomparedwiththeboundarylayerthickness.
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Asthefluidisdeflectedroundthesurface,itisacceleratedovertheleft-handsectionuntilatpositionC,thevelocityjustoutsidetheboundarylayerisamaximum.Here,thepressureisaminimum.Thus,fromAtoC,thepressuregradient�
��isnegative.
Thenetpressureforceonanelementintheboundarylayerisintheforwarddirection.BeyondpointC,however,thepressureincreases,andsothenetpressureforceonanelementintheboundarylayeropposestheforwardflow.AtpointD,thevalueof�¡
�¢atthesurfaceiszero.
Furtherdownstream,atpointE,theflowclosetothesurfacehasactuallybeenreversed.Thefluidnolongerabletofollowthecontourofthesurface,breaksawayfromit.Thisbreakawaybeforetheendofthesurfaceisreachedisusuallytermedseparation.Itfirstoccursattheseparationpointwhere �¡
�¢ ¢£¤becomezero.
Itiscausedbythereductionofvelocityintheboundarylayer,combinedwithapositivepressuregradient.
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Separationcanthereforeoccuronlywhenanadverse(positive)pressuregradientexists.Flowoveraflatplatewithzeroornegativepressuregradientwillneverseparatebeforereachingtheendoftheplate,nomatterhowlongtheplate.Inan ideal fluid,separationfromacontinuoussurfacewouldneveroccur,evenwithanadversepressuregradientbecausetherewouldbenofrictiontoproduceaboundarylayeralongthesurface.Thelineofzerovelocitydividingtheforwardandreverseflowleavesthesurfaceattheseparationpoint,and isknownas theseparationstreamline.Asaresultof thereverse flow, large irregulareddiesareformedinwhichmuchenergyisdissipatedasheat.Separationoccurswithboth laminarand turbulentboundary layer.However, laminarboundarylayersaremuchmorepronetoseparationthatturbulentones.Thisisbecauseinalaminarboundarylayer,theincreaseofvelocitywithdistancefromthesurfaceislessrapid,andtheadversepressuregradientcanmorereadilyhalttheslow-movingfluidclosetothesurface.
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A turbulent boundary layer can survive an adverse pressure gradient for some distance beforeseparating.Foranyboundarylayer,however,thegreatertheadversepressuregradient,thesoonerseparationoccurs.Theboundarylayerthickensrapidlyinanadversepressuregradient,andtheassumptionthat𝛿issmallmaynolongerbevalid.
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Inalmostallcasesinwhichflowtakesplaceroundasolidbody,theboundarylayerseparatesfromthesurfaceat somepoint.Oneexception isan infinitesimally thin flatplateparallel to themainstream.Downstreamoftheseparationpositiontheflowisgreatlydisturbedbylarge-scaleeddies,andthisregionofeddyingmotionisusuallyknownasthewake.Asaresultoftheenergydissipatedbythehighlyturbulentmotioninthewake,thepressuretherereducedandthepressuredragonthebodyisthusincreased.Themagnitudeofthepressuredragdependsverymuchonthesizeofthewakeandthis,inturn,dependsonthepositionofseparation.Iftheshapeofthebodyissuchthatseparationoccursonlywelltowardstherear,andthewakeissmall,thepressuredragisalsosmall.Suchabodyistermedastreamlinedbody.Forbluffbody,ontheotherhand,theflowisseparatedovermuchofthesurface,thewakeislargeandthepressuredragismuchgreaterthantheskinfriction.
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DEVELOPMENTOFWAKEBEHINDCYLINDERTheflowpatterninthewakedependsontheReynoldsnumberoftheflow.
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Figure(a):ForverylowReynoldsnumber 𝑅𝑒 < 0.5 ,theinertiaforcesarenegligible,andthestreamlinescometogetherbehindthecylinder.Figure(b):IfReynoldsnumberincreasedtotherange2-30,theboundarylayerseparatessymmetricallyfromthetwosidesatthepositionsS.Twoeddiesareformedwhichrotateinoppositedirections.AttheseReynoldsnumber,theyremainunchangedinposition,theirenergybeingmaintainbytheflowfromtheseparatedboundarylayer.Behindtheeddies,however,themainstreamlinescometogether.Thelengthofthewakeislimited.Figure(c):WithincreaseofReynoldsnumber,theeddieswaselongatedbutthearrangementisunstable.Figure(d):AtReynoldsnumber40-70,foracircularcylinder,aperiodicoscillationofthewakeisobserved.Then,atacertain limitingvalueofReynoldsnumber,usuallyabout90 foracircularcylinder inunconfined flow, theeddiesbreakoff fromeachsideof thecylinderalternatelyandarewasheddownstream.ThislimitingvalueofReynoldsnumberdependsontheturbulenceoftheoncomingflow,ontheshapeofthecylinderandonthenearnessofothersolidsurfaces.
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In a certain range of Reynolds number above the limiting value, eddies are continuously shedalternatelyfromthetwosidesofthecylinderand,asaresult,theyformtworowsofvorticesinitswake,thecentreofavortexinonerowbeingoppositethepointmidwaybetweenthecentresofconsecutivevorticesintheotherrow.Thisarrangementofvorticesisknownasavortexstreetorvortextrail.Von Karman considered the vortex street as a series of separate vortices in an ideal fluid anddeducedthattheonlypatternstabletosmalldisturbance,andthenonlyif:
ℎ𝑙=1𝜋𝑎𝑟𝑐𝑠𝑖𝑛ℎ1 = 0.281
Avaluelaterisconfirmedexperimentally.
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WAKEOFANAIRFOILAwakeisthedefectisstreamvelocitybehindanimmersedbodyinaflow,ashownbelow.
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Dragforcecanbewrittenas:
𝐹« = 𝐶« ∙12𝜌𝐴𝑈g
Thewakevelocitymaybewrittenas:
𝑢i𝑈¤
= 𝐶«𝑅𝑒¬16𝜋
i/g 𝐿𝑥
i/g𝑒𝑥𝑝 −
𝑈¤𝑦g
4𝑥𝜐
𝑢i = Defectvelocity
𝑈¤ = Freestreamvelocity𝜐 = Kinematicviscosityoffluid
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THECORRELATIONMETHODOFTHWAITESFromVonKarmanintegralrelation,wecanrewritethemomentumrelationinthemorecompactformas:
𝜏°𝜌𝑈g
=𝐶±2=𝑑𝜃𝑑𝑥
+ 2 + 𝐻𝜃𝑈𝑑𝑈𝑑𝑥 (Eq.4-122)
𝐻 =𝛿∗
𝜃
𝜆 =𝜃g
𝜐∙𝑑𝑈𝑑𝑥
𝜐 = Kinematicviscosity
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Multiplythemomentum-integralrelationby¶·k
𝑈𝜃𝜐
𝜏°𝜌𝑈g
=𝑈𝜃𝜐
𝑑𝜃𝑑𝑥
+𝑈𝜃𝜐
2 + 𝐻𝜃𝑈𝑑𝑈𝑑𝑥
𝜏°𝜃𝜇𝑈
=𝑈𝜃𝜐
𝑑𝜃𝑑𝑥
+𝜃g
𝜐𝑑𝑈𝑑𝑥
2 + 𝐻 (Eq.4-133)
Now,𝐻andtheleft-handsideofthisequationaredimensionlessboundarylayerfunction.Thus,byassumption,arecorrelatedreasonablybyasingleparameter(𝜆inthiscase).Thusweassume,afterHolsteinandBohlen(1940),that:
𝜏°𝜃𝜇𝑈
≈ 𝑆 𝜆 Shearcorrelation
𝐻 =𝛿∗
𝜃≈ 𝐻 𝜆 Shape-factorcorrelation
Andfurthernotethat:
𝜃𝑑𝜃 = 𝑑𝜃g
2
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Eq.4-133maythusberewrittenas:
𝑈𝑑𝑑𝑥
𝜆𝑈′
≈ 2 𝑆 𝜆 − 𝜆 2 + 𝐻 = 𝐹 𝜆 (Eq.4-135)
Whereas earlier workers would have proposed a family of profiles to evaluate the parametricfunctionsinEq.4-135,Thwaites(1949)abandonedthefavorite-familyideaandlookedattheentirecollectionofknownanalyticandexperimentalresultstoseeiftheycouldbefitbyasetofaverageone-parameterfunctions.AsshowninFigure4-22,hefoundexcellentcorrelationforthefunction𝐹 𝜆 andproposedasimplelinearfit.
𝐹 𝜆 ≈ 0.45 − 6.0𝜆 (Eq.4-136)
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If𝐹 = 𝑎 − 𝑏𝜆,Eq.4-135hasaclosed-formsolutionwhichthereadermayverifyasanexercise:
𝜃g
𝜐= 𝑎𝑈�» 𝑈»�i ∙ 𝑑𝑥 + 𝐶
�
�¼ (Eq.4-137)
If𝑥¤isastagnationpoint,theconstant𝐶mestbezerotoavoidaninfinitemomentumthicknesswhere𝑈 = 0.Thus,Thwaiteshasshownthat𝜃 𝑥 ispredictedveryaccurately(±3%),foralltypesoflaminarboundarylayers,bythesimplequadrature.
𝜃g ≈0.45𝜐𝑈¾
𝑈¿ ∙ 𝑑𝑥�
¤ (Eq.4-138)
Thwaites’suggestedcorrelationsfor𝑆 𝜆 and𝐻 𝜆 asfollows:
𝑆 𝜆 ≈ 𝜆 + 0.09 ¤.¾g (Eq.4-140)
𝐻 𝜆 ≈ 2.0 + 4.14𝑧 − 83.5𝑧g + 854𝑧� − 3337𝑧Â + 4576𝑧¿ (Eq.4-141)
𝑧 = 0.25 − 𝜆