非对称超声速喷管内流动分离非定常特性

doi:10.7527/S1000-6893.2020.24930

流体力学与飞行力学

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

非对称超声速喷管内流动分离非定常特性

何成军¹, 李建强², 黄江涛¹, 李耀华^2,3, 陈宪¹

1. 中国空气动力研究与发展中心, 绵阳 621000;
2. 中国空气动力研究与发展中心高速空气动力研究所, 绵阳 621000;
3. 南京航空航天大学航空学院, 南京 210016

收稿日期:2020-10-29 修回日期:2020-12-21 出版日期:2022-01-15 发布日期:2020-12-18
通讯作者: 黄江涛 E-mail:hjtcyf@163.com

Unsteadiness of flow separation in an asymmetric supersonic nozzle

HE Chengjun¹, LI Jianqiang², HUANG Jiangtao¹, LI Yaohua^2,3, CHEN Xian¹

1. China Aerodynamics Research and Development Center, Mianyang 621000, China;
2. High Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China;
3. College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received:2020-10-29 Revised:2020-12-21 Online:2022-01-15 Published:2020-12-18

摘要/Abstract

摘要： 综合采用流场观测和动态压力测量技术，对非对称超声速喷管分离流状态下喷管内激波结构和壁面动态压力进行了试验测量，通过壁面压力时频特性分析获得非对称喷管内不同流动分离模态的流动非定常特性。结果表明：在喷管落压比（NPR）为1.8~12.7范围内，喷管内流场结构由下偏向上偏转换；上壁面流动分离模态经历了受限激波分离（RSS）、末端振动状态和自由激波分离（FSS）；下壁面流动分离模态主要为FSS；流动分离模态为RSS时，Schmucker分离预测标准不再适用。RSS和末端振动状态模态下，尽管分离间歇区壁面动态压力具有相似的低频特征，激波运动呈显著低频特征，但末端振动状态模态下频率值略高，主要是由于流动再附点近喷管唇口，分离剪切层撞击喷管出口位置，剪切层的不稳定性影响了分离激波的振荡特性。

关键词: 非对称喷管, 受限激波分离, 末端振动状态, 非定常, 分离剪切层

Abstract: Using flow visualization and dynamic pressure measurement technology, the shock structure and dynamic pressure on the wall in an asymmetric supersonic nozzle with flow separation were experimentally measured. The time and frequency domain features of the wall pressure were analyzed to obtain the characteristics of the unsteady flow in different modes of flow separation inside the nozzle. The results show that when the Nozzle Pressure Ratio (NPR) increased from 1.8 to 12.70, the flow field structure inside the nozzle shifted from the downward to upward pattern. On the upper wall of the nozzle, there were three different modes of flow separation: Restricted Shock Separation (RSS), end effect, and Free Shock Separation (FSS). On the lower wall, the main mode of flow separation was FSS. In the RSS mode, the separation data began to deviate from the Schmucker’s criterion. In both the RSS and end effect modes, the wall in the intermittence region was under low-frequency pressure and the shock motion exhibited obvious low-frequency characteristics. In the end effect mode, the frequency value was slightly higher as the reattachment point comes in very close proximity to the nozzle lip, the separated shear layer impinges on the nozzle exit, and instability of the separated shear layer has obvious influence on motion of the separation shock.

Key words: asymmetric nozzle, restricted shock separation, end effect, unsteadiness, separated shear layer

中图分类号:

V211.3

何成军, 李建强, 黄江涛, 李耀华, 陈宪. 非对称超声速喷管内流动分离非定常特性[J]. 航空学报, 2022, 43(1): 124930-124930.

HE Chengjun, LI Jianqiang, HUANG Jiangtao, LI Yaohua, CHEN Xian. Unsteadiness of flow separation in an asymmetric supersonic nozzle[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 124930-124930.

参考文献

[1] CAPONE F J, RE R J, BARE E A. Parametric investigation of single expansion ramp nozzles at Mach numbers from 0.60 to 1.20: NASA TP-3240[R]. Washington, D.C.: NASA, 1992.
[2] MITANI T, UEDA S, TANI K, et al. Validation studies of scramjet nozzle performance[J]. Journal of Propulsion and Power, 1993, 9(5): 725-730.
[3] MIRMIRANI M, WU C, CLARK A, et al. Modeling for control of a generic airbreathing hypersonic vehicle[C]//AIAA Guidance, Navigation, and Control Conference and Exhibit. Reston: AIAA, 2005.
[4] SUMMERFIELD M, FOSTER C, SWAN W. Flow separation in overexpanded supersonic exhaust nozzles[J]. Jet Propulsion, 1954, 24(9):319-321.
[5] NAVE L, COFFEY G. Sea level side loads in high-area-ratio rocket engines[C]//9th Propulsion Conference. Reston: AIAA, 1973.
[6] AHLBERG J H, HAMILTON S, MIGDAL D, et al. Truncated perfect nozzles in optimum nozzle design[J]. ARS Journal, 1961, 31(5): 614-620.
[7] RAO G V R. Exhaust nozzle contour for optimum thrust[J]. Journal of Jet Propulsion, 1958, 28(6): 377-382.
[8] RAO G V R. Approximation of optimum thrust nozzle contours[J]. ARS Journal, 1960, 30(6): 561.
[9] DUMNOV G E. Unsteady side-load acting on the nozzle with developed separation zone: AIAA-1996-3220[R]. Reston: AIAA, 1996.
[10] FREY M, HAGEMANN G. Status of flow separation prediction in rocket nozzles[C]//34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston: AIAA, 1998.
[11] ÖSTLUND J, DAMGAARD T, FREY M. Side-load phenomena in highly overexpanded rocket nozzles[J]. Journal of Propulsion and Power, 2004, 20(4): 695-704.
[12] ENGBLOM W. Numerical prediction of SERN performance using wind code (invited)[C]//39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston: AIAA, 2003.
[13] 谭杰, 金捷, 杜刚, 等. 过膨胀单边膨胀喷管试验和数值模拟[J]. 推进技术, 2009, 30(3): 292-296. TAN J, JIN J, DU G, et al. Experimental and computational investigation of a over-expanded single-expansion-ramp-nozzle[J]. Journal of Propulsion Technology, 2009, 30(3): 292-296(in Chinese).
[14] 谭杰, 金捷, 杜刚, 等. 单边膨胀喷管试验和数值模拟[J]. 航空动力学报, 2011, 26(6): 1223-1230. TAN J, JIN J, DU G, et al. Experimental and computational investigation of single-expansion-ramp-nozzle[J]. Journal of Aerospace Power, 2011, 26(6): 1223-1230(in Chinese).
[15] YU Y, XU J L, MO J W, et al. Principal parameters in flow separation patterns of over-expanded single expansion RAMP nozzle[J]. Engineering Applications of Computational Fluid Mechanics, 2014, 8(2): 274-288.
[16] YU Y, XU J L, WANG M T. The separation pattern transition phenomena and its effects on the SERN performance[C]//18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference. Reston: AIAA, 2012.
[17] 徐惊雷, 张艳慧, 张堃元. 超燃冲压发动机非对称喷管非设计状态性能计算[J]. 推进技术, 2007, 28(3): 287-290. XU J L, ZHANG Y H, ZHANG K Y. Numerical simulation of single expansion ramp nozzle for scramjet on the off-design point[J]. Journal of Propulsion Technology, 2007, 28(3): 287-290(in Chinese).
[18] MOUSAVI S M, POURABIDI R, GOSHTASBI-RAD E. Numerical investigation of over expanded flow behavior in a single expansion ramp nozzle[J]. Acta Astronautica, 2018, 146: 273-281.
[19] 周莉, 肖华, 王占学, 等. 无源腔结构对大膨胀比单膨胀斜面喷管的影响[J]. 航空动力学报, 2015, 30(8): 1811-1817. ZHOU L, XIAO H, WANG Z X, et al. Effects of passive cavity on high pressure ratio single expansion ramp nozzle[J]. Journal of Aerospace Power, 2015, 30(8): 1811-1817(in Chinese).
[20] 周莉, 王占学, 肖华, 等. 带无源腔结构的单膨胀斜面喷管性能分析[J]. 工程热物理学报, 2015, 36(7): 1456-1460. ZHOU L, WANG Z X, XIAO H, et al. Performance analysis of single expansion ramp nozzle with passive cavity[J]. Journal of Engineering Thermophysics, 2015, 36(7): 1456-1460(in Chinese).
[21] 贺旭照, 秦思, 周凯, 等. 比热比和压比对高超飞行器尾喷流影响的实验研究[J]. 实验流体力学, 2017, 31(1): 13-19. HE X Z, QIN S, ZHOU K, et al. Experimental study of the influence of the specific heat and pressure ratios on the hypersonic vehicle’s nozzle plume[J]. Journal of Experiments in Fluid Mechanics, 2017, 31(1): 13-19(in Chinese).
[22] 贺旭照, 秦思, 卫锋, 等. 吸气式高超声速飞行器非均匀尾喷流试验[J]. 航空学报, 2017, 38(3): 120199. HE X Z, QIN S, WEI F, et al. Test of non-uniform nozzle plume for air-breathing hypersonic vehicle[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(3): 120199(in Chinese).
[23] 秦思, 贺旭照, 曾学军, 等. 喷流落压比对高超飞行器尾喷管内外流干扰的实验[J]. 航空动力学报, 2017, 32(10): 2491-2497. QIN S, HE X Z, ZENG X J, et al. Experiment of influence of the nozzle pressure ratio on the interaction between the external flow and nozzle flow of hypersonic aerocraft[J]. Journal of Aerospace Power, 2017, 32(10): 2491-2497(in Chinese).
[24] 莫建伟. TBCC排气系统设计方法及流场特性研究[D]. 南京: 南京航空航天大学, 2015. MO J W. Research on design method and flow charac-teristics of TBCC exhaust system[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2015(in Chinese).
[25] 何成军, 李建强, 范召林, 等. 单边膨胀喷管内流动分离非定常特性[J]. 航空动力学报, 2019, 34(11): 2339-2346. HE C J, LI J Q, FAN Z L, et al. Flow separation unsteadiness in single expansion ramp nozzle[J]. Journal of Aerospace Power, 2019, 34(11): 2339-2346(in Chinese).
[26] 何成军, 李建强, 范召林, 等. 过膨胀状态下单边膨胀喷管内壁面压力非定常特性试验研究[J]. 推进技术, 2020, 41(3): 537-543. HE C J, LI J Q, FAN Z L, et al. Experimental investigation of wall pressure unsteadiness in an over-expanded single expansion ramp nozzle[J]. Journal of Propulsion Technology, 2020, 41(3): 537-543(in Chinese).
[27] SCHMUCKER R H. Flow processes in overexpanded chemical rocket nozzles. Part 1: Flow separation: NASA-TM-77396[R]. Washington, D.C.: NASA, 1984.
[28] VERMA S B, MANISANKAR C. Origin of flow asymmetry in planar nozzles with separation[J]. Shock Waves, 2014, 24(2): 191-209.
[29] BARNHARDT P J, GREBER I. Experimental investiga-tion of unsteady shock wave turbulent boundary layer interactions about a blunt fin: NASA CR 202334[R]. Washington, D.C.: NASA, 2002.
[30] TAM C K W, SEINER J M, YU J C. Proposed relationship between broadband shock associated noise and screech tones[J]. Journal of Sound and Vibration, 1986, 110(2): 309-321.
[31] VERMA S, CHIDAMBARANATHAN M, HADJAD J A. Analysis of shock unsteadiness in a supersonic over-expanded planar nozzle[J]. European Journal of Mechanics - B/Fluids, 2018, 68: 55-65.
[32] DUSSAUGE J P, DUPONT P, DEBIÈVE J F. Unsteadiness in shock wave boundary layer interactions with separation[J]. Aerospace Science and Technology, 2006, 10(2): 85-91.
[33] DOLLING D S, OR C T. Unsteadiness of the shock wave structure in attached and separated compression ramp flows[J]. Experiments in Fluids, 1985, 3(1): 24-32.
[34] CHAPMAN D R, KUEHN D M, LARSON H K. Preliminary report on a study of separated flows in supersonic and subsonic streams: NACA RM-A55L14[R]. Washington, D.C.: NASA, 1956.

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

非对称超声速喷管内流动分离非定常特性

Unsteadiness of flow separation in an asymmetric supersonic nozzle

RichHTML

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	伍强, 徐浩军, 魏扬, 裴彬彬, 薛源. 结冰条件下飞机气动/运动耦合特性[J]. 航空学报, 2022, 43(8): 125566-125566.
[2]	徐欣, 贾贺, 陈雅倩, 荣伟, 蒋伟, 薛晓鹏. 织物透气性对火星用降落伞气动特性影响机理[J]. 航空学报, 2022, 43(12): 126289-126289.
[3]	罗炯, 李志宏, 陈科, 向欢. 基于嵌套网格变几何轴对称进气道非定常数值模拟[J]. 航空学报, 2022, 43(12): 627028-627028.
[4]	王宏宇, 杨彦广, 胡伟波, 陈植, 冯黎明, 周游天. 高频微秒脉冲放电控制激波/边界层干扰非定常性的实验研究[J]. 航空学报, 2022, 43(1): 625905-625905.
[5]	范孝华, 唐志共, 王刚, 杨彦广. 激波/湍流边界层干扰低频非定常性研究评述[J]. 航空学报, 2022, 43(1): 625917-625917.
[6]	沈鹏飞, 刘朋欣, 孙东, 袁先旭. 马赫6柱-裙构型激波/湍流边界层干扰摩阻统计特性[J]. 航空学报, 2022, 43(1): 626005-626005.
[7]	冈敦殿, 易仕和, 米琦, 牛海波. 超声速湍流边界层与圆柱相互作用试验[J]. 航空学报, 2022, 43(1): 626104-626104.
[8]	王德鑫, 褚佑彪, 刘难生, 李祝飞, 杨基明. 高背压进气道中内外流耦合作用的大涡模拟[J]. 航空学报, 2021, 42(9): 625754-625754.
[9]	沈恩楠, 郭同庆, 吴江鹏, 胡家亮, 张桂江. 高超声速全动翼面全时域耦合分析方法及应用[J]. 航空学报, 2021, 42(8): 525773-525773.
[10]	王延灵, 卜忱, 杨文, 沈彦杰, 冯帅. 小展弦比飞翼大迎角状态空间气动力建模[J]. 航空学报, 2021, 42(7): 124539-124539.
[11]	陈志强, 刘战合, 苗楠, 冯伟. 基于增量学习的非定常气动力参数化降阶模型[J]. 航空学报, 2021, 42(7): 125103-125103.
[12]	宋威, 张宁, 朱剑, 董垒, 蒋增辉. 风洞投放试验技术的研究现状与应用综述[J]. 航空学报, 2021, 42(6): 24417-024417.
[13]	常思源, 白晓征, 刘君. 一种基于聚类分析的二维激波模式识别算法[J]. 航空学报, 2020, 41(8): 123626-123626.
[14]	陈森林, 高正红, 朱新奇, 庞超, 杜一鸣, 陈树生. 非稳定动态过程非定常气动力建模[J]. 航空学报, 2020, 41(8): 123675-123675.
[15]	岑飞, 李清, 刘志涛, 蒋永, 张磊. 民机极限飞行状态的动态气动力试验与建模[J]. 航空学报, 2020, 41(8): 123664-123664.