高超声速气动热数值模拟方法及大规模并行计算研究

高超声速气动热数值模拟方法及大规模并行计算研究一、本文概述Overviewofthisarticle随着航空航天技术的飞速发展，高超声速飞行器的设计与研究已成为当前国际航空领域的热点和前沿。高超声速飞行器在高速飞行过程中，会受到严重的气动热影响，这不仅对飞行器的热防护设计提出了极高要求，也对气动热数值模拟的准确性和效率提出了挑战。因此，开展高超声速气动热的数值模拟方法及大规模并行计算研究，对于提高我国高超声速飞行器设计水平、推进航空航天技术的进步具有重要意义。Withtherapiddevelopmentofaerospacetechnology,thedesignandresearchofhypersonicaircrafthavebecomeahottopicandfrontierinthecurrentinternationalaviationfield.Duringhigh-speedflight,hypersonicaircraftareseverelyaffectedbyaerodynamicheat,whichnotonlyposesextremelyhighrequirementsforthethermalprotectiondesignoftheaircraft,butalsochallengestheaccuracyandefficiencyofaerodynamicthermalnumericalsimulation.Therefore,conductingnumericalsimulationmethodsandlarge-scaleparallelcomputingresearchonhypersonicaerodynamicheatisofgreatsignificanceforimprovingthedesignlevelofhypersonicaircraftinChinaandadvancingaerospacetechnology.本文首先介绍了高超声速气动热数值模拟的背景和研究意义，阐述了目前国内外在该领域的研究现状和发展趋势。接着，详细阐述了高超声速气动热的物理机制和数学模型，包括流动控制方程、热传导方程、热辐射模型等，为后续数值模拟提供了理论基础。Thisarticlefirstintroducesthebackgroundandresearchsignificanceofhypersonicaerodynamicthermalnumericalsimulation,andelaboratesonthecurrentresearchstatusanddevelopmenttrendsinthisfieldbothdomesticallyandinternationally.Subsequently,thephysicalmechanismandmathematicalmodelofhypersonicaerodynamicheatwereelaboratedindetail,includingflowcontrolequations,heatconductionequations,thermalradiationmodels,etc.,providingatheoreticalbasisforsubsequentnumericalsimulations.在数值模拟方法方面，本文重点介绍了基于有限体积法、有限差分法和谱方法等数值方法的基本原理和应用特点，分析了各种方法的优缺点和适用范围。同时，针对高超声速气动热数值模拟中遇到的关键问题，如网格生成、边界条件处理、湍流模型选择等，进行了深入讨论和研究。Intermsofnumericalsimulationmethods,thisarticlefocusesonintroducingthebasicprinciplesandapplicationcharacteristicsofnumericalmethodsbasedonfinitevolumemethod,finitedifferencemethod,andspectralmethod,andanalyzestheadvantages,disadvantages,andapplicabilityofvariousmethods.Atthesametime,in-depthdiscussionsandresearchwereconductedonkeyissuesencounteredinnumericalsimulationofhypersonicaerodynamicheat,suchasmeshgeneration,boundaryconditiontreatment,andturbulencemodelselection.在大规模并行计算方面，本文探讨了并行计算的基本原理和并行算法设计，介绍了并行计算在高超声速气动热数值模拟中的应用和优势。针对高超声速气动热数值模拟的大规模计算需求，本文提出了一种基于区域分解的并行计算策略，通过合理的任务划分和并行化技术，实现了高效的并行计算和负载均衡。Intermsoflarge-scaleparallelcomputing,thisarticleexploresthebasicprinciplesandparallelalgorithmdesignofparallelcomputing,andintroducestheapplicationandadvantagesofparallelcomputinginhypersonicaerodynamicthermalnumericalsimulation.Inresponsetothelarge-scalecomputationalrequirementsofhypersonicaerodynamicthermalnumericalsimulation,thispaperproposesaparallelcomputingstrategybasedondomaindecomposition,whichachievesefficientparallelcomputingandloadbalancingthroughreasonabletaskpartitioningandparallelizationtechniques.本文总结了高超声速气动热数值模拟方法及大规模并行计算研究的主要成果和创新点，展望了未来的研究方向和应用前景。通过本文的研究，旨在为高超声速飞行器的热防护设计和优化提供有力支持，推动我国在航空航天领域的科技进步和创新发展。Thisarticlesummarizesthemainachievementsandinnovativepointsofhypersonicaerodynamicthermalnumericalsimulationmethodsandlarge-scaleparallelcomputingresearch,andlooksforwardtofutureresearchdirectionsandapplicationprospects.Thepurposeofthisstudyistoprovidestrongsupportforthethermalprotectiondesignandoptimizationofhypersonicaircraft,andtopromotescientificandtechnologicalprogressandinnovativedevelopmentinChina'saerospacefield.二、高超声速气动热数值模拟基础理论BasicTheoryofNumericalSimulationofHypersonicAerodynamicHeat高超声速气动热数值模拟涉及复杂的物理过程和大规模计算，其基础理论主要包括流体动力学、热力学、传热学以及计算流体力学等。在这一部分，我们将详细介绍这些基础理论，以及它们在高超声速气动热数值模拟中的应用。Thenumericalsimulationofhypersonicaerodynamicheatinvolvescomplexphysicalprocessesandlarge-scalecalculations,anditsbasictheoriesmainlyincludefluiddynamics,thermodynamics,heattransfer,andcomputationalfluiddynamics.Inthissection,wewillprovideadetailedintroductiontothesefundamentaltheoriesandtheirapplicationsinhypersonicaerodynamicthermalnumericalsimulations.流体动力学是研究流体运动规律的科学，对于高超声速流动，其特点是流速极高，流场中的压力和密度变化剧烈。Navier-Stokes方程是描述粘性流体运动的基本方程，它在高超声速气动热数值模拟中发挥着核心作用。通过求解Navier-Stokes方程，可以获取流场的速度、压力、密度等关键信息。Fluiddynamicsisthescienceofstudyingthelawsoffluidmotion.Forhypersonicflow,itscharacteristicsareextremelyhighflowvelocityanddrasticchangesinpressureanddensityintheflowfield.TheNavierStokesequationisafundamentalequationthatdescribesthemotionofviscousfluidsandplaysacentralroleinhypersonicaerodynamicthermalnumericalsimulations.BysolvingtheNavierStokesequation,keyinformationsuchasvelocity,pressure,anddensityoftheflowfieldcanbeobtained.热力学是研究热现象及其转换规律的科学。在高超声速流动中，由于气流与物体表面的强烈摩擦，会产生大量的热量。热力学第一定律和第二定律为这些热量的计算提供了理论基础。同时，状态方程也是热力学中的重要工具，它描述了流体在不同温度和压力下的状态变化。Thermodynamicsisthescienceofstudyingthermalphenomenaandtheirtransformationlaws.Inhypersonicflow,alargeamountofheatisgeneratedduetothestrongfrictionbetweentheairflowandthesurfaceoftheobject.Thefirstandsecondlawsofthermodynamicsprovideatheoreticalbasisforthecalculationoftheseheats.Meanwhile,theequationofstateisalsoanimportanttoolinthermodynamics,whichdescribesthestatechangesoffluidsatdifferenttemperaturesandpressures.再次，传热学是研究热量传递规律的科学。在高超声速气动热数值模拟中，热量从气流传递到物体表面，再通过物体内部传导到其他地方。传热学中的热传导、热对流和热辐射等机制，对于准确模拟热量传递过程至关重要。Again,heattransferisthescienceofstudyingthelawsofheattransfer.Inhypersonicaerodynamicthermalnumericalsimulation,heatistransferredfromtheairflowtothesurfaceoftheobject,andthentransferredtootherplacesthroughtheinterioroftheobject.Themechanismsofheatconduction,convection,andradiationinheattransferarecrucialforaccuratelysimulatingtheprocessofheattransfer.计算流体力学（CFD）是高超声速气动热数值模拟的关键技术。它利用计算机和数值方法求解流体动力学方程，从而得到流场的详细信息。在高超声速气动热数值模拟中，CFD技术不仅可以模拟流场的运动状态，还可以计算物体表面的气动热分布。ComputationalFluidDynamics(CFD)isakeytechniquefornumericalsimulationofhypersonicaerodynamicheat.Itusescomputersandnumericalmethodstosolvefluiddynamicsequations,therebyobtainingdetailedinformationabouttheflowfield.Inthenumericalsimulationofhypersonicaerodynamicheat,CFDtechnologycannotonlysimulatethemotionstateoftheflowfield,butalsocalculatetheaerodynamicheatdistributiononthesurfaceofanobject.高超声速气动热数值模拟基础理论涉及流体动力学、热力学、传热学以及计算流体力学等多个领域。通过深入理解和应用这些基础理论，我们可以更加准确地模拟高超声速流动中的气动热现象，为相关领域的研究和应用提供有力支持。Thebasictheoryofhypersonicaerodynamicthermalnumericalsimulationinvolvesmultiplefieldssuchasfluiddynamics,thermodynamics,heattransfer,andcomputationalfluiddynamics.Bydeeplyunderstandingandapplyingthesefundamentaltheories,wecanmoreaccuratelysimulateaerodynamicthermalphenomenainhypersonicflow,providingstrongsupportforresearchandapplicationinrelatedfields.三、数值模拟方法详细研究Detailedstudyofnumericalsimulationmethods在高超声速气动热的数值模拟中，我们采用了多种复杂的计算方法，旨在更精确地模拟高超声速流动中的气动热现象。数值模拟方法的核心在于解决流动控制方程，这包括了连续性方程、动量方程、能量方程以及状态方程。考虑到高超声速流动的特殊性，如流动的不稳定性、激波的形成与传播、边界层的发展等因素，我们在数值方法的设计中进行了相应的优化和改进。Inthenumericalsimulationofhypersonicaerodynamicheat,weemployedvariouscomplexcalculationmethodstomoreaccuratelysimulatetheaerodynamicheatphenomenainhypersonicflow.Thecoreofnumericalsimulationmethodsliesinsolvingflowcontrolequations,whichincludecontinuityequations,momentumequations,energyequations,andstateequations.Consideringtheuniquecharacteristicsofhypersonicflow,suchasflowinstability,shockwaveformationandpropagation,andboundarylayerdevelopment,wehavemadecorrespondingoptimizationsandimprovementsinthedesignofnumericalmethods.在数值离散化方面，我们采用了高精度的差分格式，如迎风格式、中心差分格式以及混合格式等，以适应不同流动区域的特点。在激波捕捉方面，我们采用了激波捕捉技术，如人工粘性方法、TVD格式以及ENO/WENO格式等，以准确捕捉激波位置，减少数值耗散。Intermsofnumericaldiscretization,wehaveadoptedhigh-precisiondifferenceschemes,suchasupwindscheme,centraldifferencescheme,andhybridscheme,toadapttothecharacteristicsofdifferentflowregions.Intermsofshockwavecapture,wehaveadoptedtechniquessuchasartificialviscositymethod,TVDformat,andENO/WENOformattoaccuratelycapturetheshockwavepositionandreducenumericaldissipation.为了处理大规模并行计算，我们采用了区域分解技术，将整个计算域划分为多个子区域，每个子区域由一个计算节点独立处理。通过消息传递接口（MPI）实现节点间的数据通信和同步。我们还采用了并行计算优化策略，如负载均衡、数据局部性优化等，以提高并行计算的效率。Inordertohandlelarge-scaleparallelcomputing,weadopteddomaindecompositiontechnology,dividingtheentirecomputingdomainintomultiplesubregions,eachofwhichisindependentlyprocessedbyacomputingnode.ImplementdatacommunicationandsynchronizationbetweennodesthroughMessagePassingInterface(MPI).Wealsoadoptedparallelcomputingoptimizationstrategies,suchasloadbalancinganddatalocalityoptimization,toimprovetheefficiencyofparallelcomputing.在湍流模型方面，我们考虑了多种湍流模型，如Spalart-Allmaras模型、k-ε模型、k-ω模型以及LES/DNS方法等。根据流动的特点和计算资源的限制，我们选择了合适的湍流模型进行模拟。Intermsofturbulencemodels,wehaveconsideredvariousturbulencemodels,suchastheSpalartAllmarasmodelandk-εModel,k-ωModelsandLES/DNSmethods,etc.Basedonthecharacteristicsofflowandthelimitationsofcomputingresources,wehavechosenasuitableturbulencemodelforsimulation.为了验证数值模拟方法的准确性，我们进行了大量的算例验证和对比分析。通过与实验数据、其他数值方法的对比，验证了我们的数值模拟方法在高超声速气动热模拟中的有效性。我们也对数值模拟方法进行了误差分析和优化，以提高模拟的精度和稳定性。Inordertoverifytheaccuracyofthenumericalsimulationmethod,weconductedalargenumberofnumericalexamplesforverificationandcomparativeanalysis.Bycomparingwithexperimentaldataandothernumericalmethods,theeffectivenessofournumericalsimulationmethodinhypersonicaerodynamicthermalsimulationhasbeenverified.Wealsoconductederroranalysisandoptimizationonnumericalsimulationmethodstoimprovetheaccuracyandstabilityofthesimulation.我们在高超声速气动热的数值模拟方法中进行了深入的研究和优化，采用了高精度的数值离散化、激波捕捉技术、大规模并行计算以及合适的湍流模型等方法。这些研究成果为我们更准确地模拟高超声速流动中的气动热现象提供了有力的支持。Wehaveconductedin-depthresearchandoptimizationinthenumericalsimulationmethodsofhypersonicaerodynamicheat,usinghigh-precisionnumericaldiscretization,shockcapturetechnology,large-scaleparallelcomputing,andappropriateturbulencemodels.Theseresearchfindingsprovidestrongsupportforustomoreaccuratelysimulateaerodynamicthermalphenomenainhypersonicflow.四、大规模并行计算策略Largescaleparallelcomputingstrategy随着计算流体力学（CFD）的发展，数值模拟的规模和复杂性日益增加，对计算资源和时间的需求也越来越大。因此，为了高效地处理高超声速气动热问题，必须采用大规模并行计算策略。大规模并行计算不仅能提高计算效率，还能有效处理大规模的计算网格和复杂的物理过程。Withthedevelopmentofcomputationalfluiddynamics(CFD),thescaleandcomplexityofnumericalsimulationsareincreasing,andthedemandforcomputingresourcesandtimeisalsoincreasing.Therefore,inordertoefficientlyhandlehypersonicaerodynamicheatproblems,alarge-scaleparallelcomputingstrategymustbeadopted.Largescaleparallelcomputingcannotonlyimprovecomputationalefficiency,butalsoeffectivelyhandlelarge-scalecomputinggridsandcomplexphysicalprocesses.在大规模并行计算中，首先需要对计算任务进行合适的分解，以便在多个处理器上并行执行。对于高超声速气动热问题，我们可以将计算域划分为多个子域，每个子域由独立的处理器处理。这样可以充分利用计算资源，提高计算效率。Inlarge-scaleparallelcomputing,itisnecessarytofirstdecomposethecomputingtasksappropriatelyinordertoexecutetheminparallelonmultipleprocessors.Forhypersonicaerodynamicheatproblems,wecandividethecomputationaldomainintomultiplesubdomains,eachofwhichisprocessedbyanindependentprocessor.Thiscanfullyutilizecomputingresourcesandimprovecomputingefficiency.为了有效地进行大规模并行计算，还需要选择合适的并行算法和并行编程模型。常用的并行算法包括区域分解法、分块法等，它们能将大型问题分解为一系列小规模的子问题，并在多个处理器上并行求解。同时，我们还需要选择适合并行计算的编程模型，如MPI（MessagePassingInterface）等，以便在不同的处理器之间进行数据交换和通信。Inordertoeffectivelycarryoutlarge-scaleparallelcomputing,itisalsonecessarytochooseappropriateparallelalgorithmsandparallelprogrammingmodels.Commonparallelalgorithmsincludedomaindecompositionmethod,blockpartitioningmethod,etc.Theycandecomposelargeproblemsintoaseriesofsmall-scalesubproblemsandsolvetheminparallelonmultipleprocessors.Atthesametime,wealsoneedtochooseprogrammingmodelssuitableforparallelcomputing,suchasMPI(MessagePassingInterface),inordertoexchangeandcommunicatedatabetweendifferentprocessors.在并行计算过程中，负载均衡是一个关键的问题。如果各个处理器的负载不均衡，那么部分处理器可能会过早完成计算任务，而其他处理器则可能还在忙碌中。这会导致计算资源的浪费，降低计算效率。因此，我们需要采用适当的负载均衡策略，如动态负载均衡等，以确保各个处理器的负载相对均衡。Loadbalancingisacriticalissueinparallelcomputing.Iftheloadoneachprocessorisuneven,someprocessorsmaycompletecomputingtaskstooearly,whileothersmaystillbebusy.Thiswillleadtowastageofcomputingresourcesandreducecomputationalefficiency.Therefore,weneedtoadoptappropriateloadbalancingstrategies,suchasdynamicloadbalancing,toensurethattheloadofeachprocessorisrelativelybalanced.为了进一步提高并行计算的效率，我们还需要考虑数据通信和存储的优化。在并行计算中，各个处理器之间需要进行大量的数据通信，以交换边界条件和计算结果。如果数据通信的效率低下，那么并行计算的效率也会受到影响。因此，我们需要采用高效的数据通信策略，如非阻塞通信、重叠通信等，以减少数据通信的时间开销。我们还需要优化数据的存储方式，以便更快速地访问和更新数据。Inordertofurtherimprovetheefficiencyofparallelcomputing,wealsoneedtoconsidertheoptimizationofdatacommunicationandstorage.Inparallelcomputing,alargeamountofdatacommunicationisrequiredbetweenprocessorstoexchangeboundaryconditionsandcomputationalresults.Iftheefficiencyofdatacommunicationislow,theefficiencyofparallelcomputingwillalsobeaffected.Therefore,weneedtoadoptefficientdatacommunicationstrategies,suchasnonblockingcommunication,overlappingcommunication,etc.,toreducethetimecostofdatacommunication.Wealsoneedtooptimizethewaydataisstoredinordertoaccessandupdatedatamorequickly.大规模并行计算策略对于高效处理高超声速气动热问题具有重要意义。通过合理的任务分解、选择合适的并行算法和编程模型、采用负载均衡策略以及优化数据通信和存储方式，我们可以显著提高并行计算的效率，从而更有效地解决高超声速气动热问题。Thestrategyoflarge-scaleparallelcomputingisofgreatsignificanceforefficientlyhandlinghypersonicaerodynamicthermalproblems.Byreasonabletaskdecomposition,selectingappropriateparallelalgorithmsandprogrammingmodels,adoptingloadbalancingstrategies,andoptimizingdatacommunicationandstoragemethods,wecansignificantlyimprovetheefficiencyofparallelcomputingandmoreeffectivelysolvehypersonicaerodynamicthermalproblems.五、性能优化与效率分析Performanceoptimizationandefficiencyanalysis针对高超声速气动热数值模拟方法的性能优化与效率分析，是确保大规模并行计算有效实施的关键环节。在并行计算环境中，性能优化主要包括算法层面的优化和系统层面的优化。Theperformanceoptimizationandefficiencyanalysisofhypersonicaerodynamicthermalnumericalsimulationmethodsarecrucialtoensuretheeffectiveimplementationoflarge-scaleparallelcomputing.Inparallelcomputingenvironments,performanceoptimizationmainlyincludesalgorithmleveloptimizationandsystemleveloptimization.算法层面的优化主要关注数值方法的改进和并行策略的设计。针对高超声速气动热的特性，我们采用了隐式时间积分方法和高分辨率空间离散格式，以提高计算的稳定性和精度。同时，结合并行计算的特点，设计了基于区域分解的并行策略，将计算域划分为多个子区域，每个子区域由一个处理器独立计算，并通过消息传递接口（MPI）实现处理器之间的数据通信和同步。这种并行策略充分利用了多核处理器的计算资源，显著提高了计算的并行效率。Optimizationatthealgorithmiclevelmainlyfocusesontheimprovementofnumericalmethodsandthedesignofparallelstrategies.Weadoptedimplicittimeintegrationmethodandhigh-resolutionspatialdiscretizationschemetoimprovethestabilityandaccuracyofthecalculationforthecharacteristicsofhypersonicaerodynamicheat.Atthesametime,combiningthecharacteristicsofparallelcomputing,aparallelstrategybasedonregiondecompositionwasdesigned,dividingthecomputingdomainintomultiplesubregions,eachofwhichisindependentlycalculatedbyaprocessor,andachievingdatacommunicationandsynchronizationbetweenprocessorsthroughamessagepassinginterface(MPI).Thisparallelstrategyfullyutilizesthecomputingresourcesofmulti-coreprocessorsandsignificantlyimprovestheparallelefficiencyofcomputation.系统层面的优化则主要关注并行计算环境的配置和调优。我们通过分析计算任务的负载特性，合理分配了计算资源和内存空间，避免了资源浪费和内存溢出的问题。同时，针对并行计算中可能出现的通信瓶颈和负载不均衡等问题，我们采用了动态负载均衡和通信优化技术，确保了并行计算的稳定性和高效性。Systemleveloptimizationmainlyfocusesontheconfigurationandtuningofparallelcomputingenvironments.Wehaveallocatedcomputingresourcesandmemoryspacereasonablybyanalyzingtheloadcharacteristicsofcomputingtasks,avoidingissuesofresourcewasteandmemoryoverflow.Meanwhile,inresponsetopotentialcommunicationbottlenecksandloadimbalancesinparallelcomputing,wehaveadopteddynamicloadbalancingandcommunicationoptimizationtechniquestoensurethestabilityandefficiencyofparallelcomputing.在性能分析和效率评估方面，我们采用了多种性能指标和评估方法。通过对比不同算法和并行策略的计算结果和计算时间，我们评估了算法层面优化的效果。通过监控并行计算过程中的处理器利用率、通信开销和内存占用等指标，我们分析了系统层面优化的效果。通过综合考虑算法层面和系统层面的优化效果，我们得出了高超声速气动热数值模拟方法的整体性能提升和效率改进情况。Intermsofperformanceanalysisandefficiencyevaluation,wehaveadoptedvariousperformanceindicatorsandevaluationmethods.Weevaluatedtheeffectivenessofalgorithmleveloptimizationbycomparingthecomputationalresultsandtimeofdifferentalgorithmsandparallelstrategies.Weanalyzedtheeffectivenessofsystemleveloptimizationbymonitoringindicatorssuchasprocessorutilization,communicationoverhead,andmemoryusageduringparallelcomputing.Bycomprehensivelyconsideringtheoptimizationeffectsatthealgorithmandsystemlevels,wehaveobtainedtheoverallperformanceimprovementandefficiencyimprovementofthehypersonicaerodynamicthermalnumericalsimulationmethod.通过算法层面和系统层面的优化，以及性能分析和效率评估，我们成功实现了高超声速气动热数值模拟方法的大规模并行计算，并显著提高了计算的稳定性和效率。这为高超声速飞行器设计和优化提供了有力的数值工具和技术支持。Throughoptimizationatthealgorithmandsystemlevels,aswellasperformanceanalysisandefficiencyevaluation,wehavesuccessfullyachievedlarge-scaleparallelcomputingofhypersonicaerodynamicthermalnumericalsimulationmethods,andsignificantlyimprovedthestabilityandefficiencyofthecalculations.Thisprovidespowerfulnumericaltoolsandtechnicalsupportforthedesignandoptimizationofhypersonicaircraft.六、实际案例应用与验证Practicalcaseapplicationandverification为了验证本文所提出的高超声速气动热数值模拟方法及大规模并行计算的有效性，我们选取了两个具有代表性的实际案例进行应用与验证。Inordertoverifytheeffectivenessoftheproposedhypersonicaerodynamicthermalnumericalsimulationmethodandlarge-scaleparallelcomputing,weselectedtworepresentativepracticalcasesforapplicationandverification.针对再入飞行器在高速再入过程中所面临的严重气动热问题，我们采用了本文提出的数值模拟方法进行了热防护设计。通过模拟不同飞行条件下的气动热分布，我们优化了热防护材料的布局和结构，以降低飞行器的热负荷。并行计算技术的应用使得大规模数值模拟成为可能，大大提高了设计效率。通过与实际飞行数据的对比，验证了本文方法的有效性和准确性，为再入飞行器的热防护设计提供了有力支持。Weadoptedthenumericalsimulationmethodproposedinthispaperforthermalprotectiondesigninresponsetotheseriousaerodynamicandthermalproblemsfacedbyre-entryvehiclesduringhigh-speedre-entry.Bysimulatingtheaerodynamicheatdistributionunderdifferentflightconditions,weoptimizedthelayoutandstructureofthermalprotectionmaterialstoreducethethermalloadontheaircraft.Theapplicationofparallelcomputingtechnologymakeslarge-scalenumericalsimulationspossible,greatlyimprovingdesignefficiency.Bycomparingwithactualflightdata,theeffectivenessandaccuracyofthemethodproposedinthispaperhavebeenverified,providingstrongsupportforthethermalprotectiondesignofre-entryvehicles.为了评估高超声速飞行器在不同飞行条件下的性能表现，我们利用本文提出的数值模拟方法对其进行了性能评估。通过模拟不同马赫数、飞行高度和攻角下的气动热分布，我们分析了飞行器的热环境和热载荷变化。在大规模并行计算的支持下，我们快速获得了飞行器的性能评估结果，为飞行器的设计和优化提供了重要依据。与实验数据对比表明，本文方法的预测结果与实际情况吻合较好，具有较高的可信度。Inordertoevaluatetheperformanceofhypersonicaircraftunderdifferentflightconditions,weusedthenumericalsimulationmethodproposedinthispapertoevaluateitsperformance.BysimulatingtheaerodynamicheatdistributionatdifferentMachnumbers,flightheights,andanglesofattack,weanalyzedthethermalenvironmentandthermalloadchangesoftheaircraft.Withthesupportoflarge-scaleparallelcomputing,wequicklyobtainedtheperformanceevaluationresultsoftheaircraft,providingimportantbasisforthedesignandoptimizationoftheaircraft.Thecomparisonwithexperimentaldatashowsthatthepredictionresultsofourmethodareingoodagreementwiththeactualsituationandhavehighcredibility.通过两个实际案例的应用与验证，我们证明了本文所提出的高超声速气动热数值模拟方法及大规模并行计算的有效性和实用性。这些方法和技术为高超声速飞行器的设计和优化提供了有力支持，对于推动高超声速飞行器技术的发展具有重要意义。Throughtheapplicationandverificationoftwopracticalcases,wehavedemonstratedtheeffectivenessandpracticalityoftheproposedhypersonicaerodynamicthermalnumericalsimulationmethodandlarge-scaleparallelcomputing.Thesemethodsandtechnologiesprovidestrongsupportforthedesignandoptimizationofhypersonicaircraft,andareofgreatsignificanceforpromotingthedevelopmentofhypersonicaircrafttechnology.七、结论与展望ConclusionandOutlook本研究针对高超声速气动热的数值模拟方法及大规模并行计算进行了深入探讨。通过对不同数值方法的分析与比较，我们发现基于有限体积法的数值模拟方法在处理高超声速流场时表现出良好的稳定性和准确性。特别是在处理复杂边界条件和多物理场耦合问题时，该方法展现出了其独特的优势。我们还研究了大规模并行计算在数值模拟中的应用，显著提高了计算效率，为处理大规模、高分辨率的高超声速气动热问题提供了有效途径。Thisstudydelvesintothenumericalsimulationmethodsandlarge-scaleparallelcomputingofhypersonicaerodynamicheat.Throughtheanalysisandcomparison