空气动力学学报
空氣動力學學報
공기동역학학보
ACTA AERODYNAMICA SINICA
2014年
5期
600-609
,共10页
罗金玲%周丹%康宏琳%王济康
囉金玲%週丹%康宏琳%王濟康
라금령%주단%강굉림%왕제강
高超声速飞行器%气动性能%尖锐前缘%边界层强制转捩%风洞试验方法
高超聲速飛行器%氣動性能%尖銳前緣%邊界層彊製轉捩%風洞試驗方法
고초성속비행기%기동성능%첨예전연%변계층강제전렬%풍동시험방법
hypersonic vehicle%aerodynamic performance%sharp leading edges%boundary layer trip transition%wind tunnel experimental methods
吸气式高超声速飞行器机体与推进系统高度一体化,飞行器内外流场复杂及相互影响,地面试验模拟技术难度大,有必要开展风洞试验方法研究。本文简要分析了吸气式高超声速飞行器的主要气动问题和试验需求。针对机体/推进一体化性能试验、边界层强制转捩试验与尖锐前缘电弧风洞等三类典型试验,梳理了国内外相关风洞试验的研究思路,提出了上述三类典型风洞试验应模拟的参数,对地面试验难以模拟的重要参数进行了影响分析。根据现有试验设施的模拟能力,总结了三类典型风洞试验方法,并提出了机体/推进一体化性能数据准确获取的有效方法。
吸氣式高超聲速飛行器機體與推進繫統高度一體化,飛行器內外流場複雜及相互影響,地麵試驗模擬技術難度大,有必要開展風洞試驗方法研究。本文簡要分析瞭吸氣式高超聲速飛行器的主要氣動問題和試驗需求。針對機體/推進一體化性能試驗、邊界層彊製轉捩試驗與尖銳前緣電弧風洞等三類典型試驗,梳理瞭國內外相關風洞試驗的研究思路,提齣瞭上述三類典型風洞試驗應模擬的參數,對地麵試驗難以模擬的重要參數進行瞭影響分析。根據現有試驗設施的模擬能力,總結瞭三類典型風洞試驗方法,併提齣瞭機體/推進一體化性能數據準確穫取的有效方法。
흡기식고초성속비행기궤체여추진계통고도일체화,비행기내외류장복잡급상호영향,지면시험모의기술난도대,유필요개전풍동시험방법연구。본문간요분석료흡기식고초성속비행기적주요기동문제화시험수구。침대궤체/추진일체화성능시험、변계층강제전렬시험여첨예전연전호풍동등삼류전형시험,소리료국내외상관풍동시험적연구사로,제출료상술삼류전형풍동시험응모의적삼수,대지면시험난이모의적중요삼수진행료영향분석。근거현유시험설시적모의능력,총결료삼류전형풍동시험방법,병제출료궤체/추진일체화성능수거준학획취적유효방법。
Air-breathing hypersonic flight vehicles are highly airframe/propulsion integrated,especially the outer and inner flows of the flight vehicles are very complicated and interact strongly with each other, considerable difficulties should be solved rationally in ground testing.Therefore,it is of great necessity to conduct researches on the related experimental methodology.This paper presents a brief analysis of main aerodynamic issues concerned with air-breathing hypersonic flight vehicles as well as associated experimental testing requirements,in which three typical types of experimental testing are focused on,they are perform-ance testing of airframe/propulsion integrated vehicles,experiment of boundary layer transition with trips, and arc-heated facility testing of sharp leading edges.Besides,an overview of wind tunnel research methodol-ogies both in China and abroad is included.This paper also provides critical similarity parameters that need to be ensured for the three types of experiments mentioned above,followed by an influence analysis of those key parameters that are difficult to achieve in ground testing.Based on the testing capability of the current test facilities,three typical wind tunnel experimental methods have been put forward,along with an effective method of acquiring accurate aerodynamic performance of the airframe/propulsion integrated vehicles in par-ticular.The research materials presented should provide a useful guideline on the aerothermal and aerody-namic experimental research on hypersonic flight vehicles.