英语文章总结范文Word文件下载.docx

英语文章总结范文Word文件下载.docx

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（4）本课题的局限性、不足之处，还有哪些尚待解决的问题。

（5）展望前景，或指出进一步研究的方向。

Conclusion通常使用现在时态Result和Conclusion本次选取5篇文章，第一篇，论文中的主要Result已在第2部分和第三部分中叙述，在Conclusion又重新总结了一下。

第二篇，论文中的主要Result写在Conclusion中。

第三篇，论文中的主要Result写在第3部分（3.CASESTUDIESANDRESULTS）中，Result和Conclusion是分开的。

第四篇，论文中的主要Result已第4部分的（IV.

ResultsandDiscussion）中进行叙述，Result和Conclusion是分开的。

第五篇，论文中的主要Result已第4部分的Resultsanddiscussion）（4.

中进行叙述，Result和Conclusion是分开的。

第1篇题目：

AnoverviewofNACA6-digitairfoilseriescharacteristicswithreferencetoairfoilsforlargewindturbinebladesIV.

ConclusionsThetwo-dimensionalaerodynamicscharacteristicsoftheNACA63and64six-digitseriesofairfoilsmeasuredintheNASALTPThavebeeninvestigated,withaviewtoverifyRFOILcalculationsathighReynoldsnumbers.

Thefollowingconclusionscanbedrawn

-Thezero-liftangleoftheNACA64-618airfoilneedstobeadjustedwith-0.4degrees.

-Thezero-liftangleofTheNACA63-615needstobecorrectedwith-0.87degreesinthesmoothcaseandwith+1degreeincaseofwraparoundroughness.

-ThemaximumliftcoefficientspredictedwithRFOILmatchtheLTPTdatawellatRe=3x106,butunderpredicttheCl,maxatRe=6x106by3.5%,upto6.5%atRe=9x106.

-ItisuncertainiftheestablisheddifferencesinliftbetweenexperimentandcalculationsarecausedbyaconstantbiasinthemeasurementsorbythefactthattheRFOILcodefailstopredicttherightlevelofmaximumlift.

-RFOILconsistentlyunderpredictsthedragcoefficient.

Thedifferenceisabout9%forawiderangeofairfoilsandReynoldsnumbers-NACAstandardroughnesscausesareductionintheliftcoefficientof18%to20%formostairfoilsfromtheNACA64series-Thezero-liftangleofairfoilNACA64-418withwrap-aroundroughnessneedsacorrectionof+0.54degrees.

-Windtunnelexperimentsandside-by-sidetestsinthefieldwithonecleanrotorneedtobedonetobeabletobetterpredicttheeffectsofroughness.

写作特点

内容：

第1句，概括了文章的的主要研究内容。

第2句至第8句逐条的列出了文章的得出结论。

使用了被动语态，Thetwo-dimensionalaerodynamicscharacteristicsoftheNACA63and64six-digitseriesofairfoilsmeasuredintheNASALTPThavebeeninvestigatedhavebeeninvestigated.

主要时态为一般现在时态第2篇题目

HIGH-LIFTENHANCEMENTUSINGACTIVEFLOWCONTROLV.

CONCLUSIONSThehigh-liftperformanceofanairfoilwithasingle-elementflapisenhancedsignificantlyusinganactiveflowcontrolsystemconsistingofspanwisefluidicactuatorsthatareintegratedneartheseparationpoint.

Spanwisearraysofspanwise-oscillatingornon-oscillatingjetsissuetangentiallytothelocalsurfacefromaminiaturedownstreamfacingsurfacestep.

Jetactuationleadstoflowattachmentofvaryingstreamwiseextentthatdependsonthejetmomentumcoefficientandtheformationofalowpressuredomainnearthejuncturebetweenthemainbodyandtheflap.

Asaresult,liftisincreasedsubstantially,byasmuchas?

CL=1.40,1.22and1.04atRec=6.7?

105,8.3?

105and1.0?

106,respectively,forα=4?

.

Inthepresentexperiments,threespanwiserowsoffluidicjetsareplacedinthevicinityofthejunctureandoperatedinvariousbinationsleadingtosignificantincreasesinlift.

Theupstream（x/c=0.59）andmiddle（x/c=0.61）actuators,whichareclosesttoseparation（x/c=0.62）aremosteffective,whilethedownstreamactuator（x/c=0.64）onlyproducesasignificantliftincrementwhenoperatedinconjunctionwithoneoftheotheractuators.

Thedegreeofflowattachmentincreaseswithjetmomentumcoefficientandsimultaneousoperationofmultipleactuatorscanincreasetheliftincrementfurtherevenwhentheflowisattached.

Actuationresultsinastrongsuctionpeaknearthejuncture（Cp~?

7.5）andalsoleadstoincreasesinsuctiononthemainbodyoftheairfoilandneartheleadingedge.

Theliftincrementismeasuredoverarangeofanglesofattack（0?

<

α<

12?

）andisacpaniedbyanincreaseinlift-inducedpressuredragandanincreaseinnose-downpitchingmoment.

Itisshownthatthehigh-liftperformancecanbeimprovedsignificantlybydesignmodificationsofthesurfaceinterfacebetweenthejetactuatorsandthesurroundingflow.

Inparticular,modifyingthejetorificesfroma“stepped”toa“recessed”configurationenhancestheinteractionofthejetswiththecrossflow,resultinginincreasedliftforagivenmomentumcoefficient,particularlyatlowerlevelsofC?

Therecesseddesignalsoreducesthelossinliftcausedbythepresenceoftheorificesandtheattachedflowexhibitssignificantlystrongersuctionpeaksneartheflapjunctureandtheleadingedge.

AtC?

=0.36%theupstreamactuatoryields?

CL=0.

and0.79forthesteppedandrecessed57configurations,respectively,andoperatingthebinationofupstreamandmiddleactuatorsatC?

=0.36%eachyields?

CL=0.78and0.92,respectively.

TheeffectoftheactuatorjetsontheattachedflowischaracterizedusingPIVmeasurementsoftheflowfieldovertheflapandadditionalhigh-magnificationmeasurementsinthevicinityoftheactuators.

Intheabsenceofactuation,theflowseparatesnearthejuncturebetweentheflapandthemainbody（x/c=0.62）,formingarecirculatingdomainovertheflapandadetachedvorticitylayer.

Actuationleadstopleteflowattachmentthroughthetrailingedgewithsignificantaccelerationoftheflowwithintheattachedboundarylayerdownstreamoftheactuatorsandoutsideoftheboundarylayeralongmostoftheflap.

AtC=1.6%aninteractiondomaincontainingacross-streamvelocitypeak（~2.3timesthemaximumspeedofthejetunderquiescentconditions）isformedalongtheflapbetweentheactuatorjetandthefreestreamflowthatisparticularlyapparentusingtherecessedconfiguration.这篇文章的结论部分很特殊，统计的结果为565个单词，包含了4个段落。

第1段概括了文章的主要研究内容（activeflowcontrolsystem），第2段到第4段主要说明了文章的研究方法（experiment，PIV），以及一些具体的结果。

主要时态为一般现在时态第3篇题目

REPRESENTATIONMETHODEFFECTSONGENETICALGORITHMIN2-DAIRFOILDESIGNVIBRATIONAL4.

CONCLUSIONInthisarticle,BezierandParsecrepresentationmethodsaretestedintwodifferentflowconditions;

subsonicandtransonicflows.

InthefisttestcasebothrepresentationmethodsareparedviaVGAoptimizationtoolunderthesubsonicflowconditions.

TheparisonbetweenBezierandParsecrepresentationmethodsisshowninFig.

8.

ThisplotemphasizesthesuperiorityofParsecrepresentationmethod.

InthesecondtestcasebothrepresentationmethodsareparedviaVGAoptimizationtoolunderthetransonicflowconditions.

11.

ThisplotemphasizesthesuperiorityofBezierrepresentationmethod.

FromthesecasesitisconcludedthatParsecmethodismoreglobalandmoreefficientthanBeziermethodinsubsonicflows.

However,BeziermethodismoreflexiblethanParsecmethodwithintransonicflows.本篇文章相比于上篇文章内容上比较简短：

统计结果为134个单词，包含1个段落第1句，概括了文章的的主要研究内容。

第2句至第7句回顾了文章中的两个算例。

第8句说明了本文方法的优越性，最后一句说明了本文方法的不足。

主要时态为一般现在时态句型

Inthisarticle,TheparisonbetweenisshowninFig.

FromthesecasesitisconcludedthatHowever,第4篇题目

UnsteadyFlowSimulationofaHigh-LiftconfigurationusingaLatticeBoltzmannApproachV.

ConclusionsSimulationsofagenerichigh-liftgeometrywerecarriedoutusingtheLatticeBoltzmannbasedcodePowerFLOWwiththeframeworkofthe1stAIAACFDHighLiftPredictionWorkshopheldin20XX.

Theresultsshownhereweretheonlyunsteadysimulationsamongallworkshopparticipantsandshowexcellentagreementofdragandliftforcesaswellascpdistributionsforallworkshopcases.

GoodpredictionsintheregionofmaximumliftwereaparticularlydistinguishingfeatureoftheLatticeBoltzmannsimulations,indicatingtheimportanceofunsteadysimulationsincorrectlycapturingstronglyseparatedflowstructures.

Theslightover-predictionofcL,maxobservedforthebaselinecasewasshowntobelargelyattributabletotheabsenceofslatandflapbracketsinthesimulations.

Addingthesebrackets（Case3oftheworkshop）showsasignificantreductionofliftinparticularatthehigherangleofattack,bringingthesimulationresultstoalmostperfectagreementwithmeasuredresults.

Theeffectofchangingflapangleswasalsowellcapturedbythesimulations.

Thepositionoflaminar-to-turbulencetransitionwassetformostofthesimulationspresentedherebasedonpublishedexperimentalresultssincethemethodusedforthecurrentstudyusesawallmodelratherthanfullyresolvingtheboundarylayer.

Fullyturbulentsimulationswerecarriedoutforselectedconfigurationsandshowedasignificantreductionoflift.

Inadditiontotheworkshopcasesastudyofwindtunnelblockageeffectsisshownhere.

Addingwallsinthesimulationcorrespondingtothedimensionsofthewindtunnelledtoachangeofpredictedforcesconsistentwiththecorrectionsappliedtotheexperimentalresults.

ComputationaltimesrequiredfortheunsteadysimulationsweregenerallyinthesameorderofmagnitudeorevenslightlybelowastheRANSsimulationspresentedbyotherworkshopparticipants,confirmingthehighlevelofefficiencyoftheunsteadyLatticeBoltzmannmethod.

Overall,thismethodwasshowntobeaninterestingandviablealternativetothepredominantlyusedRANSmethodsforthesimulationofhigh-liftwings.本篇文章的结论也相对较长,统计结果为329个单词，包含4个段落第1段概括了文章的的主要研究内容。

第2段对文章中的使用的计算方法中的laminar-to-turbulencetransition进行了说明。

第3段文章中的使用的计算方法中的一点（Addingwallsinthesimulation）进行了说明。

第4段对文章的计算效率进行了说明。

进一步说明文章方法的优越性。

主要时态为一般现在时态第5篇题目

Designofanewurbanwindturbineairfoilusingapressure-loadinversemethod5.

ConclusionsApressure-loadinversedesignmethodwassuccessfullyappliedtothedesignofahigh-loadedairfoilforapplicationinasmallwindturbineforurbanenvironment.

Thepressuredistributionofthedesignedbladesectionshowsasmoothincreaseofthebladepressure-load,definedasthepressuredifferencebetweentheupperandthelowersidesofthesection,fromtheleadingedgeupto20%oftheaxialchord.

From20%upto80%oftheaxialchord,thepressure-loadisalmostconstantanditreducessmoothlytowardthetrailingedge.

Theexperimentaltestingofthenewbladesection,asanisolatedairfoil,confirmedthehighmaximumliftandamoderatedrag.

Futuredevelopmentswillconsidertheappl