Wind tunnel test technique of continuous varying Mach number for air-breathing vehicle
-
摘要: 为研究吸气式飞行器加/减速引起的进气道起动/再起动现象，以及该过程导致的飞行器整体气动性能突变问题，基于二维楔面激波机理，在1.2 m量级风洞开展超声速连续变马赫数试验技术研究，通过研制激波发生与控制系统，实现了一次风洞试验过程中马赫数连续可调。该技术方案具有马赫数调节简单、响应快，马赫数控制可靠、精度高等特点。流场校测表明，瞬时变马赫数区域流场品质满足国军标要求，可开展基于马赫数连续变化的测力测压等风洞试验。通过进气道动态特性验证试验，成功捕获了连续减速状态下进气道由起动到不起动的动态过程，临界状态特性与仿真结果一致性较高，该试验技术可为超声速吸气式飞行器进气道及整体气动性能的预测与研究提供有力支撑。Abstract: To study the start/unstart phenomenon of the air-breathing vehicle inlet caused by acceleration or deceleration, which also bring the problem of aerodynamic mutation on vehicle, the test technique of continuous varying Mach number was performed in the 1.2 m supersonic wind tunnel based on the flow mechanism of the 2D wedge shock wave. By developing the shock wave generator system, continuous varying Mach number was realized successfully in one wind tunnel test process. And it has also been confirmed that the technical method can make Mach number vary simply and quickly with high quality and precision. Through the flow-field calibration, the quality of the instantaneous flow-field in variable Mach number region meets the standards of GJB eligibly, and thus the field can be used for force and pressure test compliantly. In addition, the test of inlet starting characteristics was carried out and the dynamic process and critical state from start to unstart were captured, which indicates that the test results agree with the numerical simulation accurately. The test technique could provide effective support for supersonic air-breathing vehicle in aerodynamic performance prediction and study.
-
图 17 不同马赫数变化速率下内流道压力脉动特性
Figure 17. Characteristics of dynamic pressure with different rates of varying Mach number at internal flowpath
-
[1] WALKER S, RODGERS F, PAULL A, et al. HyCAUSE flight test program[R]. AIAA-2008-2580, 2008. [2] VOLAND R, AUSLENDER A, SMART M, et al. CIAM/NASA Mach 6.5 scramjet flight and ground test[C]//Proc of the 9th International Space Planes and Hypersonic Systems and Technologies Conference. 1999. doi: 10.2514/6.1999-4848 [3] AGRAWAL R K, YUNIS M. A generalized mathematical model to estimate gas turbine starting characteristics[C]//Proceedings of ASME 1981 International Gas Turbine Conference and Products Show. 2015. doi: 10.1115/81-GT-202 [4] 赵丽凤,王逊,刘小兵,等. 涡轮-冲压组合发动机模态过渡段性能模拟和概念探讨[J]. 工程热物理学报,1999,20(1):9-12. doi: 10.3321/j.issn:0253-231X.1999.01.003ZHAO L F,WANG X,LIU X B,et al. Performance simulation and conceptual investigation of turbo ramjet engine in transition period[J]. Journal of Engineering Thermophysics,1999,20(1):9-12. doi: 10.3321/j.issn:0253-231X.1999.01.003 [5] WIETING A R. Exploratory study of transient upstart phenomena in a three-dimensional fixed-geometry scramjet engine[R]. NASA TND-8156, 1976. [6] SHIMURA T,MITANI T,SAKURANAKA N,et al. Load oscillations caused by unstart of hypersonic wind tunnels and engines[J]. Journal of Propulsion and Power,1998,14(3):348-353. doi: 10.2514/2.5287 [7] 钟萍,陈丽艳,王颖. 国外高超声速技术焦点领域及相关设备改造综述[J]. 飞航导弹,2011(10):17-22. doi: 10.16338/j.issn.1009-1319.2011.10.013 [8] KITAMURA E, MITANI T, SAKURANAKA N, et al. Variable nozzles for aerodynamic testing of scramjet engines[C]//Proc of the ICIASF 2005 Record International Congress on Instrumentation in Aerospace Simulation Facilities. 2005: 348-354. doi: 10.1109/ICIASF.2005.1569943 [9] TICHENOR N, SEMPER M, BOWERSOX R, et al. Cali-bration of an actively controlled expansion hypersonic wind tunnel[C]//Proc of the 27th AIAA Aerodynamic Measure-ment Technology and Ground Testing Conference. 2010. doi: 10.2514/6.2010-4793 [10] GARRARD D, SEELY J, ABEL L. An analysis of alterna-tives to provide a varying Mach number test capability at APTU[C]//Proc of the 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference. 2006. doi: 10.2514/6.2006-8044 [11] 钟萍. 国外高超声速飞行加速地面模拟能力研究进展[J]. 飞航导弹,2014(6):10-15. [12] ERDMANN S F. A new economic flexible nozzle for superso-nic wind tunnels[J]. Journal of Aircraft,1971,8(1):58-60. doi: 10.2514/3.44228 [13] MACDERMOTT W N. The correction of flexible plate supersonic nozzle contours by influence methods[J]. Journal of the Aeronautical Sciences,1955,22(5):289-296. doi: 10.2514/8.3337 [14] MONTGOMERY P, GARRARD D. Test and evaluation of hypersonic aeropropulsion systems along flight trajectories in a time-varying flight environment[C]//Proc of the 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. 2005. doi: 10.2514/6.2005-3900 [15] 彭强,邓小刚,廖达雄,等. 半柔壁喷管气动设计关键控制参数研究[J]. 空气动力学学报,2011,29(1):39-46,84. doi: 10.3969/j.issn.0258-1825.2011.01.007PENG Q,DENG X G,LIAO D X,et al. The primary parameters research on the aerodynamic designing of semi-flexible nozzle[J]. Acta Aerodynamica Sinica,2011,29(1):39-46,84. doi: 10.3969/j.issn.0258-1825.2011.01.007 [16] 熊波,林学东,杨洋,等. 挠性壁喷管撑杆单位影响曲线相关性研究及其在2 m×2 m超声速风洞中的应用[J]. 实验流体力学,2013,27(4):88-91. doi: 10.3969/j.issn.1672-9897.2013.04.016XIONG B,LIN X D,YANG Y,et al. Jack's unit influence curve association study of the flexible plate nozzle and application in 2 m × 2 m supersonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics,2013,27(4):88-91. doi: 10.3969/j.issn.1672-9897.2013.04.016 [17] 范志鹏,徐惊雷,吕郑,等. 型面旋转变马赫数风洞喷管的优化设计[J]. 航空学报,2014,35(5):1216-1225.FAN Z P,XU J L,LYU Z,et al. Optimization design of variable Mach number wind tunnel nozzle by rotating profile[J]. Acta Aeronautica et Astronautica Sinica,2014,35(5):1216-1225. [18] 齐伟呈,徐惊雷,范志鹏,等. 马赫数2~4连续可调风洞数值模拟及静态标定试验[J]. 航空学报,2017,38(1):120155.QI W C,XU J L,FAN Z P,et al. Numerical simulation and experimental calibration of continuously adjustable wind tunnel with Mach number 2 to 4[J]. Acta Aeronautica et Astronautica Sinica,2017,38(1):120155. [19] 谢文忠,葛严,赵昊,等. 一种高超声速进气道加速自起动的实验方法[J]. 航空动力学报,2018,33(6):1475-1483.XIE W Z,GE Y,ZHAO H,et al. A test method for accelerating self-start of hypersonic inlets[J]. Journal of Aerospace Power,2018,33(6):1475-1483. [20] 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. doi: 10.13224/j.cnki.jasp.2015.08.007ZHAO 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. doi: 10.13224/j.cnki.jasp.2015.08.007 [21] 刘雄,王翼,梁剑寒. 二维高超声速进气道加速启动过程数值研究[J]. 推进技术,2015,36(3):328-335.LIU X,WANG Y,LIANG J H. Numerical research on accelerating start process of 2-dimensional hypersonic inlet[J]. Journal of Propulsion Technology,2015,36(3):328-335. [22] 李祝飞,高文智,杨基明. 一种二元进气道起动特性的数值与实验考察[J]. 推进技术,2016,37(7):1224-1232.LI Z F,GAO W Z,YANG J M. Numerical and experimental investigation for starting characteristics of a two-dimensional inlet[J]. Journal of Propulsion Technology,2016,37(7):1224-1232. [23] 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 [24] 张江, 董金刚, 蔡琛芳, 等. 冲压发动机进气道起动迟滞特性试验装置: 中国, CN104132811B[P]. 2016-08-24.ZHANG J, DONG J, CAI C, et al. Ramjet air inlet starting hysteresis characteristics test device: China CN104132811B[P]. 2016-08-24. [25] SHEN J M,DONG J G,LI R Q,et al. Integrated supersonic wind tunnel nozzle[J]. Chinese Journal of Aeronautics,2019,32(11):2422-2432. doi: 10.1016/j.cja.2019.07.005 [26] 中国人民解放军总装备部. 低速风洞和高速风洞流场品质要求: GJB1179A-2012[S]. 北京: 总装备部军标出版发行部, 2012. -
下载:
点击查看大图
图(20)
计量
- 文章访问数: 204
- HTML全文浏览量: 57
- PDF下载量: 8
- 被引次数: 0
