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《進(jìn)口斜激波、膨脹波干擾下等直隔離段內(nèi)的激波串特性》由會員上傳分享，免費(fèi)在線閱讀，更多相關(guān)內(nèi)容在學(xué)術(shù)論文-天天文庫。
1、第31卷2010焦第9期9月航空學(xué)報(bào)ACTAAERONAUTlCAETASTRONAUTICASINICAVoI．3lNo．9Sept．2010文章編號：1000—6893(2010)09—1733—07進(jìn)口斜激波、膨脹波干擾下等直隔離段內(nèi)的激波串特性張航，譚慧俊，孫姝(南京航空航天大學(xué)內(nèi)流研究中心，江蘇南京210016)CharacteristicsofShock-traininaStraightIsolatorwithInterferenceofIncidentShockWavesandCornerExpansionWayesZhangHang，TanHuijun，S
2、unShu(InternalFlowResearchCenter，NanjingUniversityofAeronauticsandAstronautics，Nanjing210016，China)摘要：超燃沖壓發(fā)動機(jī)的隔離段在實(shí)際工作中會受到進(jìn)氣道唇罩激波及肩部膨脹扇的顯著干擾，本文針對這一特定問題進(jìn)行了專門研究。提出了唇罩入射激波及肩部膨脹扇的模擬方法，并利用德國Achen的風(fēng)洞試驗(yàn)對其進(jìn)行了檢驗(yàn)，而后以此研究了入射激波及肩部膨脹扇干擾下隔離段內(nèi)激波串的基本形態(tài)，并分析了出口反壓和激波入射位置的影響。仿真結(jié)果表明：當(dāng)激波串在隔離段內(nèi)不斷前移時(shí)。受唇罩入射激波及其反射激
3、波的干擾，其高速核心區(qū)交替地偏向上下壁面；與無激波入射的情況相比，此時(shí)激波串的耐反壓能力顯著降低，且入射點(diǎn)位置越高，降低幅度越大，管道內(nèi)的沿程靜壓分布規(guī)律與Waltrup經(jīng)驗(yàn)公式偏離程度也越來越大。該文結(jié)果可為進(jìn)氣道／隔離段的一體化設(shè)計(jì)提供依據(jù)。關(guān)鍵詞：激波串；唇罩入射激波；肩部膨脹波；隔離段中圈分類號：V231．3文獻(xiàn)標(biāo)識碼：AAbstract：Theoperationoftheisolatorofascramjetissubstantiallyaffectedbycowlinducedshocksandcornerexpansionwaves．Thecurrentst
4、udyattemptstOrevealtheinfluenceoftheseincidentwavesontheflowpat-ternsandpressurerecoverycharacteristicsoftheshock—trainintheisolator．First，asimulationmethodfortheincidentshockandthecornerexpansionwavesisadvancedandvalidatedwithAchenwindtunnelexperimentalresultsinGermany．Then，thebasicflowp
5、atternsoftheshock—trainwiththeinfluenceoftheincidentshockwavesareanalyzed．Theeffectofthebackpressureratioandincidentpositionofthecowlinducedshockisalsoobtained．Theresultsindicatethatthesupersoniccoreflowregionoftheshock-traindeflectsalternativelytOthetopsurfaceandthebottomsurfaceoftheisol
6、atorwithitsupstreampropagationbecauseoftheinfluenceoftheincidentshockandreflectedshocks．Ascomparedwiththecasewithoutincidentshocks，thepressuregainacrosstheshock-trainissubstantiallydecreasedduetOtheincidentshockwaves．Thepressuredistributionde—viatesfromtheWaltrupempiricalformulacontinuous
7、lywiththeriseoftheincidentpointofthecowlinducedshocks．Theresultsobtainedmayprovideadesignguidefortheintegrationoftheinletandtheisolator．Keywords：shock-train，incidentshockwaves；cornerexpansionwaves；isolator作為進(jìn)氣道與燃燒室之間的氣動熱力緩沖段，隔離段是超燃沖壓發(fā)動機(jī)的重要部件。隔離段內(nèi)的超聲速流動過程是一系列以激波／邊界層干
