Suppression of Interaction Between Shock Wave and Boundary Layer for

推进技术 ›› 2014, Vol. 35 ›› Issue (9): 1153-1161.

• 气动热力学总体 • 下一篇

"X"布局高超声速倒置进气道激波与附面层干扰

郑日升¹,李伟鹏²,常军涛¹,崔佃飞³,满延进⁴,朱守梅⁴,于达仁¹,陈浮¹

哈尔滨工业大学能源学院，黑龙江哈尔滨 150001;上海交通大学航空航天学院，上海 200240;哈尔滨工业大学能源学院，黑龙江哈尔滨 150001;北京动力机械研究所，北京 100074;北京动力机械研究所高超声速冲压发动机技术重点实验室，北京 100074;北京动力机械研究所高超声速冲压发动机技术重点实验室，北京 100074;哈尔滨工业大学能源学院，黑龙江哈尔滨 150001;哈尔滨工业大学能源学院，黑龙江哈尔滨 150001

发布日期:2021-08-15
作者简介:郑日升(1981—)，男，博士生，研究领域为进气道气动分析与设计。
基金资助:
高超声速冲压发动机重点实验室开放基金(20130102006)。

Suppression of Interaction Between Shock Wave and Boundary Layer for "X" Hypersonic Inverted Inlet

Energy Science and Engineering， Harbin Institute of Technology，Harbin 150001，China;School of Aeronautics and Astronautics，Shanghai Jiao Tong University，Shanghai 200240，China;Energy Science and Engineering， Harbin Institute of Technology，Harbin 150001，China;Beijing Power Machinery Institute，Beijing 100074，China;Science and Technology on Scramjet Laboratory，Beijing Power Machinery Institute，Beijing 100074，China;Science and Technology on Scramjet Laboratory，Beijing Power Machinery Institute，Beijing 100074，China;Energy Science and Engineering， Harbin Institute of Technology，Harbin 150001，China;Energy Science and Engineering， Harbin Institute of Technology，Harbin 150001，China

Published:2021-08-15

摘要/Abstract

摘要： 采用标准k-ω SST湍流模型数值计算方法，针对二元高超声速倒置进气道激波与附面层严重的干扰现象，采用分流楔抑制激波与附面层干扰方法，对有无分流楔的进气道性能及流动机理特征进行了详细的研究。结果表明:采用分流楔的流动控制方法，有效抑制了激波/附面层产生的分离包对进气道内流动的干扰；提高倒置进气道的气动性能，进气道的总压恢复系数和流量捕获系数均有提高，计算模型的壁面总阻力系数得到一定程度的减小。数值计算结果表明，在分流楔尾迹中强剪切流动在一定程度上缓解了激波与附面层干扰的强度；在分流楔后缘存在稳定的横向涡，由于气流进入尾迹驻涡是来自附面层外的总压较高的高能流体，提高了附面层的抗逆压能力；由于尾迹驻涡的存在使得分离涡没有向弹体周向扩散，减小了阻力。该方法实现了对高超声速倒置进气道激波/附面层干扰的抑制，揭示了其抑制的机理。

关键词: 高超声速倒置进气道；激波与附面层干扰；分流楔；数值仿真；冲压发动机

Abstract: Aiming at suppression of shock wave and boundary layer interaction in two dimensional hypersonic inverted inlet，numerical simulation based on turbulent k-ω SST was performed. A suppression method was adopted to reduce the effects of the interaction shock wave and boundary layer of missile body based on the flow diverter. Inlet performance was compared and flow mechanism was studied with diverter and without diverter. Computational results indicate that the separation was suppressed with diverter，and the performance of inlet aerodynamic was improved effectively by means of this suppression method. Both the total pressure recovery coefficient and the flow coefficient of inlet increase while total drag coefficient for the wall slightly decreases. This is due to the fact that the intensity of the shock wave/ boundary layer interaction behind the diverter was reduced by the strong shear layer flow. In addition，stable transverse vortex behind the diverter is formed. It can be clearly seen that the fluid in the trail vortex is from the flow above the diverter with higher total pressure so that the capability in the transverse vortex on resisting back pressure is enhanced. Meanwhile，the flow suppression is extended along circumferential direction without diverter and this happens with diverter . This partially contributes to the reduction of drag coefficient. Based on results obtained and its mechanism analysis，it can be concluded that this method can be considered to be effective for suppression of the interaction between the shock wave and boundary layer for hypersonic inverted inlet and its suppression mechanism has been revealed.

Key words: Hypersonic inverted inlet；Shock wave/boundary layer interaction；Diverter；Numerical simulation；Ramjet engine

郑日升,李伟鹏,常军涛,崔佃飞,满延进,朱守梅,于达仁,陈浮. "X"布局高超声速倒置进气道激波与附面层干扰[J]. 推进技术, 2014, 35(9): 1153-1161.

ZHENG Ri-sheng¹,LI Wei-peng²,CHANG Jun-tao¹,CUI Dian-fei³,MAN Yan-jin⁴,ZHU Shou-mei⁴,YU Da-ren¹,CHEN Fu¹. Suppression of Interaction Between Shock Wave and Boundary Layer for "X" Hypersonic Inverted Inlet[J]. Journal of Propulsion Technology, 2014, 35(9): 1153-1161.

参考文献

[1] 万大为,郭荣伟.定几何二元倒置"X"型混压式超声速进气道数值仿真与实验验证[J].航空动力学报,2007,22(8):1279-1284.
[2] 谢文忠,郭荣伟.4种布局形式下超声速飞行器进气道气动特性实验对比[J].南京航空航天大学学报,2011,43(1):13-17.
[3] ZHU Shou-mei,CUI Dian-fei,ZHENG Ri-heng.Numerical and Experimental Investigations for a Supersonic Inlet[R].ISABE-2007-1212.
[4] 崔佃飞,朱守梅,李宏东,等.弹体附面层分流楔对倒置进气道气动性能的影响[C].乌鲁木齐:第二届冲压发动机学术会议,2007.
[5] 谭杰,金捷.跨声速和超声速流中激波/附面层干扰数值模拟[J].推进技术,2010,31(4): 394-400.(TAN Jie,JIN Jie.Numerical Simulation of Shock Wave /Turbulent Boundary-Layer Interactions in Transonic and Supersonic Flows[J].Journal of Propulsion Technology,2010,31(4): 394-400.)
[6] 潘宏禄,李俊红,沈清.超燃进气道激波/湍流附面层干扰[J].推进技术,2013,34(9): 1172-1178.(PAN Hong-lu,LI Jun-hong,SHEN Qing.Studies of Turbulence/Shock Interaction in a Scramjet Inlet[J].Journal of Propulsion Technology,2013,34(9): 1172-1178.)
[7] 刘兴洲.中国超燃冲压发动机研究回顾[J].推进技术,2008,29 (4):1001-4055.(LIU Xing-zhou,Review of Scramjet Research in China[J].Journal of Propulsion Technology,2008,29 (4): 385-395.)
[8] 董志勇,吕阳泉.激波与附面层干扰研究综述[J].浙江工业大学学报,2001,29(3): 295-300.
[9] 王振锋,白菡尘,桂业伟.高超声速进气道外压缩面激波附面层干扰研究回顾[C].无锡:第三届高超声速科技学术会议,2010.
[10] 王翼.高超声速进气道启动问题研究[D].长沙:国防科学技术大学,2008.
[11] Syberg J,Hickcox T E.Design of a Bleed System for a Mach 3.5 Inlet[R].NASA CR-2187,1973.
[12] Harloff G J,Smith G E.On Supersonic Inlet Boundary Layer Bleed Flow[R].AIAA 95-0038.
[13] Schulte D,Henckels A,Wepler U.Reduction of Shock induced Boundary Layer Separation in Hypersonic Inlets Using Bleed[J].Aerospace Science and Technology,1998,2(4):231-239.
[14] 严红明,钟兢军,韩吉昂,等.超声速进气道喉部附面层抽吸[J].推进技术,2009,30(2): 175-181.(YAN Hong-ming,ZHONG Jing-jun,HAN Ji-ang,et al.Research on Boundary Layer Suction in the Throat of Supersonic Inlet[J].Journal of Propulsion Technology,2009,30(2):175-181.)
[15] Caraballo E,Webb N,Little J,et al.Supersonic Inlet Flow Control Using Plasma Actuators[R].AIAA 2009-924.
[16] Seong-kyun Im,Hyungrok Do,Godfrey M,et al.Experimental Study and Plasma Control of an Unstarting Supersonic Flow[R].AIAA 2012-2809.
[17] Webb N,Clifford C,Samimy M.Control of Oblique Shock wave/Boundary Layer Interactions Using Plasma Actuators[R].AIAA 2012-2810.
[18] Bisek N J,Rizzetta D P,Poggie J.Plasma Control of a Turbulent Shock Boundary-Layer Interaction[J].AIAA Journal,2013,51(8): 1789-1804.
[19] 王博.基于微型涡流发生器的激波/附面层干扰控制研究[D].长沙: 国防科学技术大学,2010.
[20] Rybalko M,Babinsky H,Loth E.Vortex Generators for a Normal Shock/Boundary Layer Interaction with a Downstream Diffuser[J].Journal of Propulsion and Power,2012,28(1): 71-82.
[21] Titchener N,Babinsky H.Shock Wave/Boundary-Layer Interaction Control Using a Combination of Vortex Generators and bBleed[J].AIAA Journal,2013,51(5): 1221-1233.
[22] 张悦,谭慧俊,张启帆,等.一种进气道内激波/附面层干扰控制的新方法及其流动机理[J].宇航学报,2013 ,33(2): 265-274.
[23] 苏纬仪,张堃元,金志光.一种抑制激波-附面层相互作用的新型无源被动控制[J].空气动力学学报,2011,29(6): 738-742.
[24] Schülein E.Optical Skin Friction Measurements in Short-duration Facilities[R].AIAA 2004-2115.(编辑:张荣莉)收稿日期:2014-01-13；修订日期:2014-03-20。基金项目:高超声速冲压发动机重点实验室开放基金(20130102006)。作者简介:郑日升(1981—),男,博士生,研究领域为进气道气动分析与设计。E-mail:zhengrisheng2000@163.com

"X"布局高超声速倒置进气道激波与附面层干扰

Suppression of Interaction Between Shock Wave and Boundary Layer for "X" Hypersonic Inverted Inlet

PDF

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 0

编辑推荐

Metrics

本文评价