实验流体力学
實驗流體力學
실험류체역학
JOURNAL OF EXPERIMENTS IN FLUID MECHANICS
2014年
3期
39-44
,共6页
贺旭照%周正%毛鹏飞%乐嘉陵
賀旭照%週正%毛鵬飛%樂嘉陵
하욱조%주정%모붕비%악가릉
乘波体%进气道%一体化设计%密切内锥%流线追踪%试验研究
乘波體%進氣道%一體化設計%密切內錐%流線追蹤%試驗研究
승파체%진기도%일체화설계%밀절내추%류선추종%시험연구
waverider%inlet%integration design%osculating inward turning cone%streamline tracing%experimental study
介绍了密切曲面内锥乘波前体进气道(Osculating Inward turning Cone Waverider Inlet,OICWI)的一体化设计方法,对该型乘波前体进气道的性能进行了数值分析,针对该型一体化乘波前体进气道完成了风洞试验研究。理论设计结果和设计状态无粘模拟结果一致,设计状态下的计算结果表明,前体进气道具有较高的总压恢复、较好出口流场均匀度及较高的流量捕获率。试验研究结果表明,改型一体化前体进气道在马赫数5~7条件下顺利启动,流场波系及压力分布同数值分析结果吻合。
介紹瞭密切麯麵內錐乘波前體進氣道(Osculating Inward turning Cone Waverider Inlet,OICWI)的一體化設計方法,對該型乘波前體進氣道的性能進行瞭數值分析,針對該型一體化乘波前體進氣道完成瞭風洞試驗研究。理論設計結果和設計狀態無粘模擬結果一緻,設計狀態下的計算結果錶明,前體進氣道具有較高的總壓恢複、較好齣口流場均勻度及較高的流量捕穫率。試驗研究結果錶明,改型一體化前體進氣道在馬赫數5~7條件下順利啟動,流場波繫及壓力分佈同數值分析結果吻閤。
개소료밀절곡면내추승파전체진기도(Osculating Inward turning Cone Waverider Inlet,OICWI)적일체화설계방법,대해형승파전체진기도적성능진행료수치분석,침대해형일체화승파전체진기도완성료풍동시험연구。이론설계결과화설계상태무점모의결과일치,설계상태하적계산결과표명,전체진기도구유교고적총압회복、교호출구류장균균도급교고적류량포획솔。시험연구결과표명,개형일체화전체진기도재마혁수5~7조건하순리계동,류장파계급압력분포동수치분석결과문합。
An integration design method of osculating inward turning cone waverider inlet (OICWI)are put forward in the paper.The performance of a typical inlet designed by the method has been validated by numerical simulation and wind tunnel tests.The waverider inlet integration design method of OICWI is conceived based on osculation axisymmetric and stream line tracing theory.The basic flowfield was firstly conducted by Method of Characteristics (MOC)and basic inner compression cone,then the inlet configuration was induced by streamline tracing technique. At the same time,theoretic characteristic of the inlet was calculated by MOC.The accurate per-formance of the OICWI is analyzed using Computational Fluid Dynamics (CFD)software.De-tailed flowfield simulation results were directly compared to experimental data to evaluate the accuracy of the numerical model and provide insight into the experimental flowfield behavior.The experiment study was fulfilled in China Aerodynamics Research and Development Center (CRADC)’sΦ0.5m hypersonic wind tunnel.The numerical/experimental results analyses show that the design method of OICWI is reasonable.The inviscid numerical simulation results agree well with theoretical design results in the design condition.The numerical simulation results show that OICWI has high pressure recovery in design and off-design condition.The flowfield be-havior obtained by CFD indicates that the isolate exit flow field has benign uniformity and OICWI has high flow capture ratio.The experimental results show that the OICWI can start from Mach number 5 to 7 .The flow field structure and pressure distribution agree well with numerical anal-ysis results.