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Flow response hysteresis of throat regulation process of a two-dimensional mixed-compression supersonic inlet

Chinese Journal of Aeronautics 2022年第3期35卷 112-127页

作者： Yi JIN Shu SUN Huijun TAN Yue ZHANG Hexia HUANG Jiangsu Province Key Laboratory of Aerospace Power System College of Energy and Power EngineeringNanjing University of Aeronautics and AstronauticsNanjing 210016China

The variable geometry supersonic inlet tends to decrease the throat area to reduce the Mach number upstream of the terminal shock,so as to reduce the flow loss.However,excessive Internal Contraction Ratio(ICR)exposes the inlet to a greater risk of unstart,which inevitably results in a process of increasing the throat area to aid the inlet restart.In the above throat regulation process,the inlet undergoes the start,unstart,and restart states in turn.In order to reveal the flow structure and mechanism of this process,a two-dimensional unsteady numerical simulation combined with a dynamic mesh technique were employed.The shock-on-lip Mach number of the studied inlet is 4.0 and the flight angle of attack is+6°.Analysis was focused on the state with a freestream Mach number of 3.0.The results clearly show that the flow response hysteresis appears,and restart is only realized when the throat area is obviously increased as compared to that of unstart due to the historical unstart flow structure.In addition,three typical flow fields were analyzed,and it is found that the separation ahead of the inlet was the key factor affecting the hysteresis.Finally,unstart and restart boundaries of the inlet were discussed,and the factors influencing its deviation from the typical boundaries of dual-solution area were analyzed.The newly predicted unstart and restart boundaries are much closer to the CFD results.

关键词： Hysteresis Restart Supersonic inlet Throat regulation process unstart Unsteady numerical simulation

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Performance of wavecatcher intakes at angles of attack and sideslip

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Chinese Journal of Aeronautics 2021年第7期34卷 244-256页

作者： Fengyuan ZUO Sannu MO LDER Gang CHEN State Key Laboratory for Strength and Vibration of Mechanical Structures School of Aerospace EngineeringXi’an Jiaotong UniversityXi’an 710049China Ryerson University Toronto ON M5B 2K3Canada

A wavecatcher type scramjet intake,that reduces the Mach number number from 4 to 1.552,is used as the basis for a study of flow starting/unstarting as affected by freestream angles of attack and sideslip.The intake design is based on a morphed streamtube consisting of two conical flow streamlines using streamline tracing and osculating axisymmetric design theory.Intake flow and performance is modeled using the numerical CFD code and the k-e turbulence model.The intake unstarts at a sideslip angle of 2,a positive angle of attack of 1.Both positive angle of attack and sideslip angle have an adverse effect on the startability of the MBus intake.At negative angles,the intake initially unstarts at5angle of attack,due to the thickened shear layer induced by the streamwise vortex.Then it re-starts at8angle of attack,mainly due to the expansion fan formed at the leading edge,causing the shock wave structures inside the intake to be reestablished.

关键词： Angle of attack Sideslip angle unstart Wavecatcher intake

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反压引起超声速进气道不起动和再起动特性研究

反压引起超声速进气道不起动和再起动特性研究

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中国航天第三专业信息网第三十八届技术交流会暨第二届空天...

作者：汪昆谢旅荣刘雨南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室

为了研究反压突变过程中超声速进气道不起动和再起动特性,对二元超声速进气道进行了非定常数值模拟,分析了设计工况下不同降压时间和降压值对进气道流场和再起动特性的影响。结果表明:当反压从32P的不起动流场降至24P时,不同降压时间对... 详细信息

为了研究反压突变过程中超声速进气道不起动和再起动特性,对二元超声速进气道进行了非定常数值模拟,分析了设计工况下不同降压时间和降压值对进气道流场和再起动特性的影响。结果表明:当反压从32P的不起动流场降至24P时,不同降压时间对进气道再起动效果有直接影响,降压时间越短,对进气道再起动越有利,而降压时间过长,进气道无法实现再起动;随着反压降压值增加,进气道实现再起动的最大降压时间随之增加,当反压降压值和降压时间都较大时,进气道实现再起动前会出现短时间回流;降压时间和降压值共同影响进气道再起动特性。

关键词： supersonic inlet backpressure unstart restart numerical simulation

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