Variable angle of attack start experiment of 2D curved compression inlet
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摘要: 开展了内外压缩型面可控的弯曲压缩进气道反设计方法研究,并针对设计的二元弯曲压缩进气道进行了不同马赫数下变攻角起动数值仿真及试验研究,获得了进气道起动攻角迟滞环,仿真与试验得到的不起动/自起动攻角、出口流场以及压力分布吻合良好,同时试验结果也表明设计的弯曲压缩进气道具有较高的综合气动特性,设计点Ma=4、α=3°抗反压能力70倍来流压力以上,总压恢复系数在0.5以上。Abstract: The reverse design method of curved compression inlet with controllable internal and external compression surfaces was studied, the numerical simulation and experimental study of the designed 2D curved compression inlet starting with varying angle of attack at different Mach numbers were carried out, and the hysteresis loop of the inlet starting angle of attack was obtained. Simulation and experiment indicated that unstarting/self-starting angle of attack, the outflow field and pressure distribution coincided well, and the experiment results also showed that curved compression inlet had high comprehensive aerodynamic characteristics; at design points Ma=4, α=3° back pressure resistance ability was more than 70 times of inflow pressure, total pressure recovery coefficient was above 0.5.
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Key words:
- curved compression /
- inlet start /
- reverse design /
- wind tunnel experiment /
- hysteresis phenomenon
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[1] EDWARDS C L W,SMAll W J,WEIDNER J P,et al.Studies of scramjet/airframe integration techniques for hypersonic aircraft[R].AIAA 75-58,1975. [2] 张堃元.基于弯曲激波压缩系统的高超声速进气道反设计研究进展[J].航空学报,2015,36(1):274-288. ZHANG Kunyuan.Research progress on hypersonic inlet reverse design based on curved shock compression system[J].Acta Aeronautica et Astronautica Sinica,2015,36(1):274-288.(in Chinese) [3] 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. NAN Xiangjun,ZHANG Kunyuan,JIN Zhiguang,et al.Investigation on hypersonic inward turning inlets with controlled pressure gradient[J].Journal of Aerospace Power,2011,26(3):518-523.(in Chinese) [4] WANG Lei,ZHANG Kunyuan,NAN Xiangjun,et al.Optimization and experimental investigation of 2-D hypersonic curved shock[R].AIAA-2012-5959,2012. [5] 王磊,张堃元,向有志,等.高超声速二元弯曲激波压缩面反设计方法的参数化研究[J].南京航空航天大学学报,2013,45(4):441-446. WANG Lei,ZHANG Kunyuan,XIANG Youzhi,et al.2-D hypersonic curved shock compression surface[J].Journal of Nanjing University of Aeronautics and Astronautics,2013,45(4):441-446.(in Chinese) [6] 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. LI Yongzhou,ZHANG Kunyuan,NAN Xiangjun.Design of hypersonic inward turning inlets base on concept of controllable Mach number distribution[J].Journal of Aerospace Power,2012,27(11):2484-2491.(in Chinese) [7] 朱伟.基于马赫数分布规律的高超矩形转圆内转式进气道设计研究[D].南京:南京航空航天大学,2012. ZHU Wei.Investigation on hypersonic rectangular to circle shape transition inward turning inlets with controlled Mach number distributions[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2012.(in Chinese) [8] 朱伟,张堃元,南向军.壁面马赫数分布规律可控的新型内收缩基准流场设计方法[J].推进技术,2013,34(4):433-438. ZHU Wei,ZHANG Kunyuan,NAN Xiangjun.Investigation on basic flowfield with controlled Mach number gradient for hypersonic inward turning inlets[J].Journal of Propulsion Technology,2013,34(4):433-438.(in Chinese) [9] 张林,张堃元,王磊,等.基于壁面马赫数梯度的高超声速弯曲激波二维进气道数值研究[J].航空动力学报,2013,28(4):752-758. ZHANG Lin,ZHANG Kunyuan,WANG Lei,et al.Computational investigation of hypersonic curved shock two-dimensional inlet with compression surface constant Mach number gradient[J].Journal of Aerospace Power,2013,28(4):752-758.(in Chinese) [10] 周硕,张堃元,王磊.高超压缩面分段反设计研究[R].北京:高超声速专题研讨会暨第5届全国高超声速科学技术会,2012. [11] VAN WIE D,KWOK F T,WALSH R F.Starting characteristics of supersonic inlet[R].AIAA 96-2914,1996. [12] 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 Yi.Investigation on the starting characteristics of hypersonic inlet[D].Changsha:National University of Defense Technology,2008.(in Chinese) [13] 余安远,乐嘉陵.高超声速进气道起动问题的二维数值模拟初探[R].南京:高超声速进气道技术交流(研讨)会,2005. [14] 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 Zhufei,GAO Wenzhi,YANG Jiming.Numerical and experimental investigation for starting characteristics of a two-dimensional inlet[J].Journal of Propulsion Technology,2016,37(7):1224-1232.(in Chinese) [15] 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 Xiong,WANG Yi,LIANG Jianhan.Numerical research on accelerating starting of 2-dimensional hypersonic inlet[J].Journal of Propulsion Technology,2015,36(3):328-335.(in Chinese) [16] 游进,夏智勋,王登攀,等.高超声速进气道再起动特性及其影响因素数值模拟[J].固体火箭技术,2011,34(2):161-166. YOU Jin,XIA Zhixun,WANG Dengpan,et al.Numerical study on influencing factors of restarting characteristics for a hypersonic inlet[J].Journal of Solid Rocket Technology,2011,34(2):161-166.(in Chinese) [17] 岳连捷,刘红,徐骁,等.激波风洞进气道自起动实验方法[C]∥第9届全国实验流体力学学术会议论文集.杭州:中国力学学会,2013:29-35. [18] WANG Yi,WANG Zhenguo,LIANG Jianhan,et al.Investigation on hypersonic inlet starting process in continuous freejet wind tunnel[J].Journal of Propulsion and Power,2014,30(6):1721-1726. [19] GRAINGER A L,BOYCE R R,TIRTEY S C,et al.The unsteady flow physics of hypersonic inlet starting processes[R].AIAA-2012-5937,2012. [20] 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 Wenzhong,GE Yan,ZHAO Hao,et al.A test method for accelerating self-start of hypersonic inlets[J].Journal of Aerospace Power,2018,33(6):1475-1483.(in Chinese) [21] 徐尚成,王翼,苏丹,等.迎角变化引起的高超声速进气道起动迟滞现象试验研究[J].实验流体力学,2019,33(3):76-82. XU Shangcheng,WANG Yi,SU Dan,et al.Experimental study on hysteresis phenomenon of hypersonic inlet caused by variation of angle of attack[J].Journal of Experiments in Fluid Mechanics,2019,33(3):76-82.(in Chinese)
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