高超声速内转式进气道流动的壁面丝线显示

推进技术 ›› 2017, Vol. 38 ›› Issue (7): 1475-1482.

高超声速内转式进气道流动的壁面丝线显示

李祝飞¹,黄蓉¹,郭帅涛¹,詹东文¹,刘坤伟¹,吴颖川²,余安远²,杨基明¹

中国科学技术大学近代力学系，安徽合肥 230027,中国科学技术大学近代力学系，安徽合肥 230027,中国科学技术大学近代力学系，安徽合肥 230027,中国科学技术大学近代力学系，安徽合肥 230027,中国科学技术大学近代力学系，安徽合肥 230027,中国空气动力研究与发展中心吸气式高超声速技术研究中心，四川绵阳 621000,中国空气动力研究与发展中心吸气式高超声速技术研究中心，四川绵阳 621000,中国科学技术大学近代力学系，安徽合肥 230027

发布日期:2021-08-15
作者简介:李祝飞，男，博士后，研究领域为高超声速进气道。
基金资助:
国家自然科学基金(11402263；11132010)；中国博士后科学基金(2014M551818)。

Surface Tuft Flow Visualization in Hypersonic Inward Turning Inlet

Department of Modern Mechanics，University of Science and Technology of China，Hefei 230027，China,Department of Modern Mechanics，University of Science and Technology of China，Hefei 230027，China,Department of Modern Mechanics，University of Science and Technology of China，Hefei 230027，China,Department of Modern Mechanics，University of Science and Technology of China，Hefei 230027，China,Department of Modern Mechanics，University of Science and Technology of China，Hefei 230027，China,Air-Breathing Hypersonic Technique Research Center of China Aerodynamics Research and Development Center，Mianyang 621000，China,Air-Breathing Hypersonic Technique Research Center of China Aerodynamics Research and Development Center，Mianyang 621000，China and Department of Modern Mechanics，University of Science and Technology of China，Hefei 230027，China

Published:2021-08-15

摘要/Abstract

摘要： 针对风洞实验观测高超声速内转式进气道内部流动困难，不易获得内流道三维激波/边界层干扰主导的复杂流场结构的问题，通过拓展壁面丝线流动显示技术的潜力，在[Ma∞5.9]激波风洞中，借助高速摄影实时拍摄丝线流谱，并结合纹影、壁面压强测量以及数值模拟分析，验证了丝线的动态响应特性，丰富了内转式进气道的观测技术，获得了进气道的流场结构。采用预设堵块实验方法，在激波风洞中考核了内转式进气道模型的自起动能力。结果表明，直径约为0.1 mm，长度约为15 mm的402号涤纶/棉缝纫线的跟随性较好，能够直观、动态地显示出壁面流动分离区的范围，为判断内转式进气道是否起动提供了依据。内转式进气道模型在实验条件下能够自起动，起动状态下进气道唇口附近的波系结构以及前体压缩面的丝线流谱和压力分布与数值模拟符合较好。

关键词: 内转式进气道；数值模拟；激波风洞实验；壁面丝线流动显示；自起动

Abstract: Due to the difficulty in observing the internal flow of a hypersonic inward-turning inlet in wind tunnels，the flow structure of the three-dimensional shock wave/boundary layer interactions in such an inward-turning inlet cannot be obtained easily. The surface tuft flow visualization technique was extended，and then applied in a shock tunnel with a freestream Mach number of 5.9 to obtain the flow structure in an inward-turning inlet. With the help of a high-speed camera to monitor flow patterns of the surface tuft in real time，Schlieren associated with surface pressure measurement and analysis of numerical simulations and the dynamic response characteristics of the tuft was confirmed. The surface tuft flow visualization technique enriches the observation methods of the inward-turning inlet. To detect the inlet self-starting ability in the shock tunnel，a testing method of pre-setting a blockage in the inlet was used. The results indicate that the tuft of 402 polyester cotton sewing thread with a diameter of approximately 0.1mm and a length of approximately 15mm has fast?tracking ability?to intuitively and dynamically display the flow separation region on the inlet wall，which is proof of its good ability to indicate the start/unstart of the inward-turning inlet. The inward-turning inlet model is able to self-start at the test flow conditions. When the inlet is started，the shock structure near the cowl，the surface tuft flow patterns and the pressure distribution on the forebody agree well with the numerical simulations.

Key words: Inward turning inlet；Numerical simulation；Shock tunnel experiment；Surface tuft flow visualization；Self-starting

李祝飞,黄蓉,郭帅涛,詹东文,刘坤伟,吴颖川,余安远,杨基明. 高超声速内转式进气道流动的壁面丝线显示[J]. 推进技术, 2017, 38(7): 1475-1482.

LI Zhu-fei¹,HUANG Rong¹,GUO Shuai-tao¹,ZHAN Dong-wen¹,LIU Kun-wei¹,WU Ying-chuan²,YU An-yuan²,YANG Ji-ming¹. Surface Tuft Flow Visualization in Hypersonic Inward Turning Inlet[J]. Journal of Propulsion Technology, 2017, 38(7): 1475-1482.

参考文献

[1] Kothari A P, Tarpley C, McLaughlin T A, et al. Hypersonic Vehicle Design Using Inward Turning Flow Fields [R]. AIAA 1996-2552.
[2] You Y. An Overview of the Advantages and Concerns of Hypersonic Inward Turning Inlets[R]. AIAA 2011-2269.
[3] Walker S H, Rodgers F. Falcon Hypersonic Technology Overview[R]. AIAA 2005-3253.
[4] Walker S H, Rodgers F, Esposita A L. Hypersonic Collaborative Australia/United States Experiment (HYCAUSE) [R]. AIAA 2005-3254.
[5] Holden M S, Smolinski G J, Mundy E, et al. Experimental Studies for Hypersonic Vehicle Design and Code Validation of the Unsteady Flow Characteristics Associated with “Free Flight” Shroud and Stage Separation, and Mode Switching [R]. AIAA 2008-642.
[6] Stephen E J, Hoenisch S R, Waddel M L, et al. HIFiRE 6 Unstart Conditions at Off-Design Mach Numbers [R]. AIAA 2015-0109.
[7] Steelant J, Langener T, Hannemann K, et al. Conceptual Design of the High-Speed Propelled Experimental Flight Test Vehicle HEXAFLY [R]. AIAA 2015-3539.
[8] Hannemann K, Schramm J M, Karl S, et al. Free Flight Testing of a Scramjet Engine in a Large Scale Shock Tunnel [R]. AIAA 2015-3608.
[9] M?lder S, Szpiro E J. Busemann Inlet for Hypersonic Speeds [J]. Journal of Spacecraft and Rockets, 1966, 3(8): 1303-1304.
[10] Billig F S, Kothari A P. Streamline Tracing: Technique for Designing Hypersonic Vehicles[J]. Journal of Propulsion and Power, 2000, 16(3): 465-471.
[11] Smart M K. Design of Three-Dimensional Hypersonic Inlets with Rectangular-to-Elliptical Shape Transition [J]. Journal of Propulsion and Power, 1999, 15(3): 408-416.
[12] Sabean J W, Lewis M J. Computational Optimization of a Hypersonic Rectangular-to-Circular Inlet[J]. Journal of Propulsion and Power, 2001, 17(3): 571-578.
[13] Smart M K, Trexler C A. Mach 4 Performance of Hypersonic Inlet with Rectangular-to-Elliptical Shape Transition[J]. Journal of Propulsion and Power, 2004, 20(2): 288-293.
[14] Doherty L J, Smart M K, Mee D J. Experimental Testing of an Airframe-Integrated Three-Dimensional Scramjet at Mach 10[J]. AIAA Journal, 2015, 53(11): 3196-3207.
[15] 孙波, 张堃元, 金志光, 等. 流线追踪Busemann进气道设计参数的选择[J]. 推进技术, 2007, 28(1): 55-59. (SUN Bo, ZHANG Kun-yuan, JIN Zhi-guang, et al. Selection of Design Parameters for Stream Traced Hypersonic Busemann Inlets[J]. Journal of Propulsion Technology, 2007, 28(1): 55-59.)
[16] 南向军, 张堃元, 金志光, 等. 压升规律可控的高超声速内收缩进气道设计[J]. 航空动力学报, 2011, 26(3): 518-523.
[17] 李永洲, 张堃元, 南向军. 基于马赫数分布规律可控概念的高超声速内收缩进气道设计[J]. 航空动力学报, 2012, 27(11): 2484-2491.
[18] 李永洲, 张堃元, 朱伟, 等. 双弯曲入射激波的可控中心体内收缩基准流场设计[J]. 航空动力学报, 2015, 30(3): 563-570.
[19] 尤延铖, 梁德旺, 黄国平. 一种新型内乘波式进气道初步研究[J]. 推进技术, 2006, 27(3): 252-256. (YOU Yan-cheng, LIANG De-wang, HUANG Guo-ping. Investigation of Internal Waverider-Derived Hypersonic Inlet[J]. Journal of Propulsion Technology, 2006, 27(3): 252-256.)
[20] 朱呈祥, 黄国平, 尤延铖, 等. 内乘波式进气道与典型侧压式进气道的性能对比[J]. 推进技术, 2011, 32(2): 151-158. (ZHU Cheng-xiang, HUANG Guo-ping, YOU Yan-cheng, et al. Performance Comparison between Internal Waverider Inlet and Typical Sidewall Compression Inlet[J]. Journal of Propulsion Technology, 2011, 32(2): 151-158.)
[21] 卫锋, 贺旭照, 贺元元, 等. 三维内转式进气道对双旁进气飞行器力矩特性的影响分析[J]. 推进技术, 2014, 35(11): 1441-1447. (WEI Feng, HE Xu-zhao, HE Yuan-yuan, et al. Effects Analysis of 3D Inward Turning Inlet on Moment Characteristics of Vehicle with Inlets Decorated in Both Sides [J]. Journal of Propulsion Technology, 2014, 35(11): 1441-1447.)
[22] 卫锋, 贺旭照, 贺元元, 等. 三维内转式进气道双激波基准流场的设计方法[J]. 推进技术, 2015, 36(3): 358-364. (WEI Feng, HE Xu-zhao, HE Yuan-yuan, et al. Design Method of Dual-Shock Wave Basic Flow-Field for Inward Turning Inlet [J]. Journal of Propulsion Technology, 2015, 36(3): 358-364.)
[23] 刘雄, 王翼, 梁剑寒. 方转圆对三维侧压进气道的流动特性影响[J]. 航空学报, 2014, 35(11): 2939-2948.
[24] 肖雅彬, 岳连捷, 张新宇. 利用NURBS中心锥消除马赫盘的内转式进气道设计方法 [C]. 三亚:第四届高超声速科技学术会议, 2011.
[25] 徐锦, 罗金玲, 戴梧叶, 等. 三维内收缩前体/进气道设计参数影响规律研究[J]. 空气动力学学报, 2014, (05): 646-653.
[26] 王德鹏, 田方超, 张启帆, 等. 进口形状对内转式进气道的起动特性影响[J]. 航空动力学报, 2015, 30(6): 1400-1406.
[27] 杨大伟, 余安远, 韩亦宇, 等. 泄流对高超声速内转式进气道自起动性能影响研究[C]. 哈尔滨:第八届全国高超声速科技学术会议, 2015.
[28] Jacobsen L S, Tam C, Behdadnia R, et al. Starting and Operation of a Streamline-Traced Busemann Inlet at Mach 4 [R]. AIAA 2006-4508.
[29] Flock A K, Gülhan A. Experimental Investigation of the Starting Behavior of a Three-Dimensional Scramjet Intake [J]. AIAA Journal, 2015, 53(9): 2686-2693.
[30] 范洁川. 近代流动显示技术[M]. 北京:国防工业出版社, 2002.
[31] Shapiro A H. Design of Tufts for Flow Visualization[J]. AIAA Journal, 1963, 1(1): 213-214.
[32] Crowder J P. Flow Visualization in Flight Testing[R]. AlAA 1990-1273.
[33] 李福忠, 王晓东. 流动显示学在风机领域中的最新进展(之一)论丝线的动态响应及方向分布定量计算[J]. 风机技术, 1995, 05: 6-11.
[34] Zaidi H, Taiar R, Fohanno S, et al. Surface Flow Visualization around Competitive Swimmers by Tufts Method[J]. Journal of Visualization, 2008, 11(3): 187-188.
[35] Wieser D, Bonitz S, Nayeri C N, et al. Quantitative Tuft Flow Visualization on the Volvo S60 Under Realistic Driving Conditions [R]. AIAA 2016-1778.
[36] Crowder J P. Add Fluorescent Minitufts to the Aerodynamicist's Bag of Tricks [J]. Astronautics and Aeronautics, 1980, 18: 54-56.
[37] 吴根兴, 汪子兴. 观察物体表面附近流谱的新方法——萤光微丝法[J]. 南京航空航天大学学报, 1980, 04: 102-110.
[38] 惠增宏, 侯金玉, 邓磊. 荧光微丝在低速风洞试验中应用的关键技术研究[J]. 实验流体力学, 2015, 29(1): 92-96.
[39] Stephen C, Jewel B. Investigation of Critical States of the F/A-18E in Power Approach Configuration Using Mini-Tuft Flow Visualization [R]. AIAA 2001-4145.
[40] Pittman J L. Experimental Flowfield Visualization of a High Alpha Wing at Mach 1.62[J]. Journal of Aircraft, 1987, 24(5): 335-341.
[41] Album H H. Hypersonic Flow Visualization Using Tufts of Pure Carbon Yarn [J]. AIAA Journal, 1965, 3(8): 1520.
[42] Kammeyer M E, Lafferty J F, Spring W C. (1989). Microtuft Flow Visualization at Mach 10 and 14 in the NSWC Hypervelocity Wind Tunnel No.9 [R]. AIAA 1989-41
[43] 黄舶, 李祝飞, 杨基明, 等. 激波风洞内超燃冲压发动机三面压缩进气道流场实验观测[J]. 实验力学, 2012, 27(1): 23-29.
[44] 黄舶. 高超声速内外流动激波/边界层相互作用的实验与数值研究[D]. 合肥:中国科学技术大学, 2013.
[45] 余安远, 杨大伟, 卫锋, 等. 典型高超声速内转式进气道性能研究[C]. 哈尔滨:第八届全国高超声速科技学术会议, 2015.
[46] Zhufei Li, Wenzhi Gao, Hongliang Jiang, et al. Unsteady Behaviors of a Hypersonic Inlet Caused by Throttling in Shock Tunnel[J]. AIAA Journal, 2013, 51(10): 2485-2492.
[47] 李祝飞, 高文智, 李鹏, 等. 二元高超声速进气道激波振荡特性实验 [J]. 推进技术, 2012, 33(5): 676-682. (LI Zhu-fei, GAO Wen-zhi, LI Peng, et al. Experimental Investigation on the Shock Wave Oscillation Behaviors in a Two-Dimensional Hypersonic Inlet Flow[J]. Journal of Propulsion Technology, 2012, 33(5): 676-682.)
[48] Li Z, Huang B, Yang J. A Novel Test of Starting Characteristics of Hypersonic Inlets in Shock Tunnel[R]. AIAA 2011-2308.
[49] 李祝飞, 杨基明. 预设堵块法检测进气道自起动能力的数值研究[J]. 推进技术, 2016, 37(10). (LI Zhu-fei, YANG Ji-ming. A Numerical Investigation of the Pre-Setting-Blockage Method to Detect the Self-Starting Ability of an Inlet[J]. Journal of Propulsion Technology, 2016, 37(10).)
[50] 陈强. 激波管流动的理论和实验技术[M]. 合肥:中国科学技术大学五系讲义, 1979.
[51] 李祝飞. 高超声速进气道起动特性机理研究[D]. 合肥:中国科学技术大学, 2013.
[52] 李祝飞, 高文智, 李鹏, 等. 一种进气道自起动特性检测方法[J]. 实验流体力学, 2013, 27(2): 14-18.
[53] 刘启国, 侯秀良, 张新龙. 竹炭涤纶纤维的热学性能浅析[J]. 毛纺科技, 2009, 37(9): 44-46.　　　　　　　　　　　　　　收稿日期:2016-03-21；修订日期:2016-05-05。基金项目:国家自然科学基金(11402263；11132010)；中国博士后科学基金(2014M551818)。作者简介:李祝飞,男,博士后,研究领域为高超声速进气道。 E-mail: lizhufei@mail.ustc.edu.cn(编辑:朱立影)