侧滑角对鼓包诱导曲面激波/边界层干扰特性的影响

高婉宁; 张悦; 谭慧俊; 殷宁

doi:10.13224/j.cnki.jasp.2019.05.014

侧滑角对鼓包诱导曲面激波/边界层干扰特性的影响

doi: 10.13224/j.cnki.jasp.2019.05.014

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,南京 210016

基金项目: 自然基金青年基金（51806102）; 中国博士后科学基金（2016M600412）

计量
- 文章访问数: 851
- HTML浏览量: 81
- PDF量: 477
- 被引次数: 0
出版历程
- 收稿日期: 2018-12-06
- 刊出日期: 2019-05-28

Characteristics of bump induced curved shock/boundary layer interaction under the sideslip condition

摘要

摘要: 利用仿真方法对侧滑条件下设计马赫数为2的三维壁面鼓包诱导流场进行了研究。结果表明：随着侧滑角的增大,迎风面的展向压力梯度增大,鼓包表面高压中心向迎风面偏移使得迎风面前缘旋涡强度增强,迎风侧出口总压恢复损失,最终导致鼓包下游流场畸变增加。同时鼓包表面流动拓扑结构表明,随着侧滑角的增加，迎风面分离区的准锥形相似特性增强,而背风面由准锥形相似逐渐发展为准柱形相似。
- 侧滑条件 /
- 鼓包 /
- bump进气道 /
- 压力梯度 /
- 曲面激波/边界层干扰
Abstract: The simulation method was used to investigate the flow field around the three-dimensional surface bump at designed Mach number 2 under the sideslip condition. Results show that as the sideslip angle increases, the pressure gradient on the windward side increases, and the high pressure center of the bump surface shifts toward the windward side. As a result, the strength of the vortex near the bump leading edge increases,which causes the loss of the total pressure recovery at windward side and finally makes the distortion of bump downstream flow field increase. At the same time, the surface flow topology of the bump shows that the conical similarity of the windward side separation zone increases as the sideslip angle increase, while the separation region on the bump leeward side evolves from a quasi-conical similarity to a quasi-cylindrical similarity gradually.
- sideslip condition /
- bump /
- bump inlet /
- pressure gradient /
- curved shock wave/boundary layer interactions

HTML

参考文献(19)

[1]	HEHS E.JSF diverterless supersonic inlet［R］.Washington DC:Lockheed Martine Aeronautics Company,2000.
[2]	杨应凯,李玉璞.JSF X-35的一绝—无附面层隔道超音速进气道［J］.国际航空,2001(8):13-15.YANG Yingkai,LI Yupu.Diverterless supersonic inlet of JSF X-35［J］.International Aviation,2001(8):13-15.(in Chinese)
[3]	HAMSTRA J W,MCCALLUM B N,MCFARLAN J D.Development,verification,and transition of an advanced engine inlet concept for combat aircraft application［R］.Lockheed Martin Aerospace Company Paper MP-121-P-43,2003.
[4]	杨应凯.枭龙飞机Bump进气道设计［J］.南京航空航天大学学报,2007,39(4):449-452.YANG Yingkai.Design of Bump inlet of thunder/JF-17 aircraft［J］.Journal of Nanjing University of Aeronautics and Astronautics,2007,39(4):449-452.(in Chinese)
[5]	梁德旺,李博.无隔道进气道反设计及附面层排除机理分析［J］.航空学报,2005,26(3):286-289.LIANG Dewang,LI Bo.Reverse design of diverterless inlet and mechanism of diversion of boundary layer［J］.Acta Aeronautica et Astronautica Sinica,2005,26(3):286-289.(in Chinese)
[6]	SEDDON J,GOLDSMITH E L.Intake aerodynamics［M］.London:Collins Professional and Technical Books,1985.
[7]	钟易成,余少志,吴晴.凸包(Bump)进气道/DSI模型设计及气动特性研究［J］.航空动力学报,2005,20(5):740-746.ZHONG Yicheng,YU Shaozhi,WU Qing.Research of Bump inlet/DSI model design and its aerodynamic properties［J］.Journal of Aerospace Power,2005,20(5):740-746.(in Chinese)
[8]	杨应凯.Bump进气道设计与试验研究［J］.空气动力学学报,2007,25(3):336-338,350.YANG Yingkai.The research of Bump inlet design and test［J］.Acta Aerodynamica Sinica,2007,25(3):336-338,350.(in Chinese)
[9]	HAMSTRA J W,MCCALLUM B N,SYLVESTER T G,et al.Transition shoulder system and method for diverting boundary layer air:US5749542［P］.1998-05-12.
[10]	KIM S D.Aerodynamic design of a supersonic inlet with a parametric bump［J］.Journal of Aircraft,2009,46(1):198-202.
[11]	SVENSSON M.A CFD investigation of a generic Bump and its application to a diverterless supersonic inlet［D］.Norrkping,Sweden:Linkping University,2008.
[12]	蔡乐.Bump进气道的机理与设计规律研究［D］.哈尔滨：哈尔滨工业大学,2009.CAI Le.The mechanism of bump inlet and its design laws［D］.Harbin:Harbin Institute of Technology,2009.(in Chinese)
[13]	王娇,谭慧俊,黄河峡.不同波系配置的鼓包压缩面引起的激波/边界层干扰特性［J］.航空动力学报,2018,33(2):372-382.WANG Jiao,TAN Huijun,HUANG Hexia.Characteristic of shock wave/boundary layer interactions induced by bumps with different shock wave system arrangements［J］.Journal of Aerospace Power,2018,33(2):372-382.(in Chinese)
[14]	王娇.Bump进气道内激波/边界层干扰特性研究［D］.南京：南京航空航天大学,2017.WANG Jiao.Research on characteristics of shock wave/boundary layer interactions in bump inlet［D］.Nanjing:Nanjing University of Aeronautics and Astronautics,2017.(in Chinese)
[15]	符小刚,于芳芳,王玲玲.进气角度对蚌式进气道与发动机相容性的影响［J］.燃气涡轮试验与研究,2016,29(5):1-4.FU Xiaogang,YU Fangfang,WANG Lingling.Effects of intake angle to compatibility of bump inlet and engine［J］.Gas Turbine Experiment and Research,2016,29(5):1-4.(in Chinese)
[16]	PANARASA G.Numerical investigation of the high-speed conical flow past a sharp fin［J］.Journal of Fluid Mechanics,1992,236:607-633.
[17]	ALVI F S,SETTLES G S.Physical model of the swept shock wave/boundary-layer interaction flowfield［J］.AIAA Journal,1992,30(9):2252-2258.
[18]	PIROZZOLI S,BERNARDINI M,GRASSO F,et al.Direct numerical simulation of transonic shock/boundary layer interaction under conditions of incipient separation［J］.Journal of Fluid Mechanics,2010,657:361-393.
[19]	FANG J,YAO Y,ZHELTOVODOV A A,et al.Investigation of three-dimensional shock wave/turbulent-boundary-layer interaction initiated by a single fin［J］.AIAA Journal,2017,55(2):509-523.