Experimental study on hysteresis phenomenon of hypersonic inlet caused by variations of angle of attack
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摘要: 高超声速进气道在起动过程中存在迟滞现象，起动迟滞对发动机的工作范围有重要影响。以一种Bump/前体一体化进气道为研究对象，通过试验和数值仿真结合的方法，研究迎角变化引起的进气道起动迟滞现象。试验在国防科技大学LF-220自由射流风洞中进行，来流条件Ma=5.0，采用蓄热式加热器对上游气流进行加热，稳定段总压1.59MPa，试验段静温91.67K。试验模型由底座、进气道前体前锥、进气道前体后锥和唇罩4部分组成，模型总长度285mm。采用PSI压力传感器对模型壁面压力进行测量，采样频率为100Hz。试验成功捕捉到进气道随迎角变化由不起动转化为起动的动态过程。研究表明，高超声速进气道随迎角变化存在明显的迟滞现象。试验获得进气道自起动迎角为-1.3°，而进气道自不起动迎角大于10°。在进气道自起动/自不起动过程的研究中发现，随着进气道流动状态的不同，迎角和大尺度分离区交替主导流量变化。Abstract: Hysteresis phenomenon occurs in the process of hypersonic inlet start, which has an important influence on the working range of the scramjet. In this paper, a hypersonic inlet is introduced, and the inlet hysteresis caused by variations of angle of attack is studied by experiment and numerical simulation. The experiment is conducted in a free-jet wind tunnel LF-220 of NUDT (National University of Defense Technology) at Ma=5.0. The regenerative electric heater is used to heat the high-pressure airflow. The total pressure in the settling chamber is 1.59MPa, and the static temperature in the test section is 91.67K. The model is constituted of the first part of forebody, the second part of forebody, the cowl and the lampstand. The pressure sensors are used to measure the wall pressure at a frequency of 100Hz. The dynamic process from unstart to start with the change of angle of attack is captured in the experiment, and the self-starting/-unstarting performances are obtained. The results show that a significant hysteresis occurs in hypersonic inlets with the change of angle of attack. In the experiment, the self-starting angle of attack is -1.3°, while the self-unstarting angle of attack is larger than 10°. In the study of the self-starting/-unstarting process, it is found that the angle of attack and the large-scale separation zone alternately dominate the mass flow.
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Key words:
- hypersonic inlet /
- angle of attack /
- hysteresis phenomenon /
- separation zone /
- mass flow
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图 4 进气道迎角起动试验过程中对称面纹影图(试验1)
Figure 4. Schlieren images on different attack angles during the starting process (first experiment)
图 5 进气道迎角起动试验过程中对称面纹影图(试验2)
Figure 5. Schlieren images on different attack angles during the starting process (second experiment)
图 6 不同迎角状态下进气道壁面沿程压力分布
Figure 6. Wall pressures along flow direction with different angles of attack
图 7 模型迎角增大过程中流场结构变化图
Figure 7. Schlieren images with different angles of attack during the self-unstarting process
图 8 进气道起动流场对称面纹影数值与试验结果对比
Figure 8. Schlieren images of starting inlet showing comparison of the numerical simulation with the experiment data
图 9 进气道起动流场对称面压力分布数值与试验结果对比
Figure 9. Wall pressure distribution of starting inlet showing comparison of the numerical simulation with the experiment data
图 10 进气道不起动流场对称面纹影数值与试验结果对比
Figure 10. Schlieren images of unstarting inlet showing comparison of the numerical simulation with the experiment data
图 11 进气道不起动流场对称面压力分布数值与试验结果对比
Figure 11. Wall pressure distribution of unstarting inlet showing comparison of the numerical simulation with the experiment data
图 12 进气道迎角自起动/自不起动过程中进气道内通道测点压力试验和数值计算结果
Figure 12. Wall pressure at internal section of the inlet in the process of self-starting/-unstarting
图 13 进气道自起动((a)，从左至右)/自不起动过程((b)，从右至左)对称面马赫数分布
Figure 13. Mach number distributions on the symmetry planes in the self-starting process ((a), from left to right) and the self-unstarting process ((b), from right to left)
图 14 进气道自起动/自不起动过程中流量变化
Figure 14. Mass flow in the process of self-starting/-unstarting
表 1 进气道自起动迎角第1次试验时序设定
Table 1. Time sequence of the first experiment in the self-starting process
迎角/(°) 8.0 4.0 0 -0.5 -1.0 -1.5 -2.0 停留时间/s 3 1 1 1 1 1 1 
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表 2 进气道自起动迎角第2次试验时序设定
Table 2. Time sequence of the second experiment in the self-starting process
迎角/(°) 8.0 4.0 0 -0.5 -1.0 -1.1 -1.2 -1.3 停留时间/s 3 1 1 1 1 1 1 1
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表 3 进气道自不起动迎角试验时序设定
Table 3. Time sequence of the experiment in the self-unstarting process
迎角/(°) -1.5 0 2.5 5.0 7.5 10.0 停留时间/s 3 1 1 1 1 1
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[1] Seddon J, Goldsmith E L. Intake aerodynamics[M]. 2nd ed. Reston:American Institute of Aeronautics and Astronautics, 1999. [2] Rozario D, Zouaoui Z. Computational fluid dynamic analysis of scramjet inlet[R]. AIAA-2007-30, 2007. [3] Van Wie D, Kwok F T, Walsh R F. Starting characteristics of supersonic inlet[R]. AIAA-1996-2914, 1996. [4] 王翼.高超声速进气道启动问题研究[D].长沙: 国防科技大学, 2008.Wang Y. Investigation on the starting characteristics of hypersonic inlet[D]. Changsha: National University of Defense Technology, 2008. [5] 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, 23. doi: 10.3969/j.issn.1672-9897.2013.02.003Li Z F, Gao W Z, Li P, et al. A test method for inlet self-starting ability detection[J]. Journal of Experiments in Fluid Mechanics, 2013, 27(2):14-18, 23. doi: 10.3969/j.issn.1672-9897.2013.02.003 [6] Cui T, Lv Z, Yu D R. Multistability and complex routes of supersonic start/unstart[J]. Journal of Propulsion and Power, 2011, 27(6):1204-1217. doi: 10.2514/1.B34235 [7] Wang W X, Guo R W. Numerical study of unsteady starting characteristics of a hypersonic inlet[J]. Chinese Journal of Aeronautics, 2013, 26(3):563-571. doi: 10.1016/j.cja.2013.04.018 [8] 赵昊, 谢旅荣, 郭荣伟, 等.超声速进气道加速/减速过程起动/不起动现象研究[J].航空动力学报, 2015, 30(8):1841-1852. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=hkdlxb201508007Zhao H, Xie L R, Guo R W, et al. Study of start/unstart phenomenon of supersonic inlet in acceleration/deceleration process[J]. Journal of Aerospace Power, 2015, 30(8):1841-1852. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=hkdlxb201508007 [9] 郭帅涛, 李祝飞, 高文智, 等.攻角与马赫数对进气道起动影响的可比拟性[J].推进技术, 2017, 38(5):983-991. http://d.old.wanfangdata.com.cn/Periodical/tjjs201705004Guo S T, Li Z F, Gao W Z, et al. Analogy between effects of attack angle and Mach number on inlet starting[J]. Journal of Propulsion Technology, 2017, 38(5):983-991. http://d.old.wanfangdata.com.cn/Periodical/tjjs201705004 [10] 常军涛, 于达仁, 鲍文.攻角引起的高超声速进气道不起动/再起动特性研究[J].航空动力学报, 2008, 23(5):816-821. http://www.cnki.com.cn/Article/CJFDTOTAL-HKDI200805006.htmChang J T, Yu D R, Bao W. Characteristic analysis of unstart/restart of hypersonic inlets caused by variations of attack angle of freestream[J]. Journal of Aerospace Power, 2008, 23(5):816-821. http://www.cnki.com.cn/Article/CJFDTOTAL-HKDI200805006.htm [11] 常军涛.高超声速进气道起动/不起动模式分类及控制[D].哈尔滨: 哈尔滨工业大学, 2007. http://www.wanfangdata.com.cn/details/detail.do?_type=degree&id=D272306Chang J T. Pattern classification and control of hypersonic inlet start/unstart[D]. Harbin: Harbin institute of Technology, 2007. http://www.wanfangdata.com.cn/details/detail.do?_type=degree&id=D272306 [12] Chang J T, Li N, Xu K J, et al. Recent research progress on unstart mechanism, detection and control of hypersonic inlet[J]. Progress in Aerospace Sciences, 2017, 89:1-22. doi: 10.1016/j.paerosci.2016.12.001 [13] 王翼, 徐尚成, 王振国, 等.一种带边界层排移的轴对称预压缩前体的设计方法: CN107628266A. 2018-01-26. [14] 徐尚成, 王翼, 王振国, 等. Bump/前体一体化对高速进气道起动特性的影响研究[J].推进技术, 2019, 40(4):780-785. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=tjjs201904007Xu S C, Wang Y, Wang Z G, et al. Research on starting of high speed inlet with integrated Bump/forebody[J]. Journal of Propulsion Technology, 2019, 40(4):780-785. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=tjjs201904007 [15] 王小虎, 易仕和, 付佳, 等.带气膜冷却结构的高超声速平板不同前缘形状下表面传热特性研究[J].实验流体力学, 2015:29(2):19-25. http://www.syltlx.com/CN/abstract/abstract10821.shtmlWang X H, Yi S H, Fu J, et al. Study of surface heat transfer characteristics of hypersonic flat plate with film-cooling structure under different leading edge shape conditions[J]. Journal of Experiments in Fluid Mechanics, 2015, 29(2):19-25. http://www.syltlx.com/CN/abstract/abstract10821.shtml [16] 徐尚成.高超声速进气道Bump/前体一体化设计与研究[D].长沙: 国防科技大学, 2018.Xu S C. Design and analysis of hypersonic inlet with integrated Bump/forebody[D]. Changsha: National University of Defense Technology, 2018. -
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