一种高超声速进气道加速自起动的实验方法
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摘要
为了探寻在地面常规暂冲式风洞中开展高超声速进气道加速自起动实验的可行性,提出了基于前遮板的高超声速进气道连续变攻角加速自起动实验方法。该实验方法通过将安装有前遮板的进气道模型在风洞实验段整体从极限正攻角旋转至极限负攻角,前遮板会产生激波对远前方气流减速,或产生膨胀波对远前方气流加速,而位于前遮板下游的进气道即可获得加速自起动过程所需连续加速的来流条件。通过数值仿真对所提出的加速自起动实验方法进行了验证。研究结果显示:以2(°)/s的角速度整体旋转基于前遮板的高超声速进气道模型,其起动马赫数与高超声速进气道自身加速自起动马赫数相差在1%以内,表明基于前遮板的高超声速进气道连续变攻角加速自起动实验方法能够被用于在常规暂冲式风洞中开展高超声速进气道加速自起动实验研究。
To explore the feasibility of testing the accelerating self-start ability of hypersonic inlets in a blow-down wind tunnel,a self-starting test method based on continuous varying attack angle of a shielding plate fixed on the upstream hypersonic inlets was developed.In the test,the hypersonic inlet,together with a shielding plate,rotated from the limiting positive attack angle to the limiting negative attack angle.The shielding plate decelerated the freestream by shock wave,or accelerated the freestream by expansion waves.Hence,the continuous accelerating freestream downstream the shielding plate can be obtained for the inlet.The test method was verified with numerical simulations.Results show that:the devia-tion of the starting Mach number in the rotating process of the hypersonic inlet with a shielding plate at an angular velocity of 2(°)/s and the inlet self-starting Mach number is within1%,indicating that the method based on the continuous varying attck angle of a hypersonic inlet with a shielding plate can be used to test the self-starting ability of hypersonic inlets in a blow-down wind tunnel.
To explore the feasibility of testing the accelerating self-start ability of hypersonic inlets in a blow-down wind tunnel,a self-starting test method based on continuous varying attack angle of a shielding plate fixed on the upstream hypersonic inlets was developed.In the test,the hypersonic inlet,together with a shielding plate,rotated from the limiting positive attack angle to the limiting negative attack angle.The shielding plate decelerated the freestream by shock wave,or accelerated the freestream by expansion waves.Hence,the continuous accelerating freestream downstream the shielding plate can be obtained for the inlet.The test method was verified with numerical simulations.Results show that:the devia-tion of the starting Mach number in the rotating process of the hypersonic inlet with a shielding plate at an angular velocity of 2(°)/s and the inlet self-starting Mach number is within1%,indicating that the method based on the continuous varying attck angle of a hypersonic inlet with a shielding plate can be used to test the self-starting ability of hypersonic inlets in a blow-down wind tunnel.
引文
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[12]岳连捷,刘红,徐骁,等.激波风洞进气道自起动实验方法[C]∥第九届全国实验流体力学学术会议论文.杭州:中国力学学会,2013:29-35.
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[15]张来平,邓小刚,张涵信.动网格生成技术及非定常计算方法进展综述[J].力学进展,2010,40(4):424-447.ZHANG Laiping,DENG Xiaogang,ZHANG Hanxin.Reviews of moving grid generation techniques and numerical methods for unsteady flow[J].Advances in Mechanics,2010,40(4):424-447.(in Chinese)
[16]王卫星,郭荣伟.高超进气道自起动过程中流动非定常特性[J].航空学报,2015,36(10):3263-3274.WANG Weixing,GUO Rongwei.The unsteady flow characteristics of hypersonic inlet during self-starting[J].Acta Aeronautica et Astronautica Sinica,2015,36(10):3263-3274.(in Chinese)
[17]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)
[18]WANG Zhenguo,ZHAO Yilong,ZHAO Yuxin,et al.Prediction of massive separation of unstarted inlet via free-interaction theory[J].AIAA Journal,2015,53(4):1108-1112.
[19]陈卫明.二元高超声速进气道自起动特性的影响因素分析[D].南京:南京航空航天大学,2013.CHEN Weiming.Analysis of the influencing factors on two-dimensional hypersonic inlet self-starting characteristics[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2013.(in Chinese)
[20]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)
[2]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 start process of 2-dimensional hypersonic inlet[J].Journal of Propulsion Technology,2015,36(3):328-335.(in Chinese)
[3]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)
[4]WANG Jianyong,XIE Lürong,ZHAO Hao,et al.A fluidic control method for improving the self-starting ability of hypersonic inlets[J].Journal of Propulsion and Power,2016,32(1):153-160.
[5]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.
[6]VAN WIE D M,KWOK F T,WALSH R F.Starting characteristics of supersonic inlets[R].AIAA 96-2914,1996.
[7]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.
[8]徐骁,岳连捷,卢洪波,等.高超声速进气道快速破膜开启的流动特性[J].航空学报,2015,36(6):1795-1804.XU Xiao,YUE Lianjie,LU Hongbo,et al.Flow characteristics of hypersonic inlet starting with diaphragm rupture[J].Acta Aeronautica et Astronautica Sinica,2015,36(6):1795-1804.(in Chinese)
[9]凌岗,李祝飞,肖丰收,等.一种二元高超声速进气道起动特性的尺度效应研究[J].实验流体力学,2014,28(3):26-31.LING Gang,LI Zhufei,XIAO Fengshou,et al.Scale effects on the starting characteristics of a 2Dhypersonic inlet[J].Journal of Experiments in Fluid Mechanics,2014,28(3):26-31.(in Chinese)
[10]凌岗,李祝飞,肖丰收,等.低雷诺数下进气道异常起动现象及其影响因素探析[J].实验流体力学,2014,28(4):9-15.LING Gang,LI Zhufei,XIAO Fengshou et al.An exploration on the unusual self-starting behaviors of a hypersonic inlet under low Reynolds number[J].Journal of Experiments in Fluid Mechanics,2014,28(4):9-15.(in Chinese)
[11]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.LI Zhufei.An investigation on starting characteristics of hypersonic inlets[D].Hefei:University of Science and Technology of China,2013.(in Chinese)
[12]岳连捷,刘红,徐骁,等.激波风洞进气道自起动实验方法[C]∥第九届全国实验流体力学学术会议论文.杭州:中国力学学会,2013:29-35.
[13]BUTTSWOITH D R,SMART M K.Development of a Ludwieg tube with free piston compression heating for scramjet inlet starting expenments[R].AIAA-2010-588,2010.
[14]RODI P E,EMAMI S,TREXLER C A.Unsteady pressure behavior in a ramjet/scramjet inlet[J].Journal of Propulsion and Power,1996,12(3):486-493.
[15]张来平,邓小刚,张涵信.动网格生成技术及非定常计算方法进展综述[J].力学进展,2010,40(4):424-447.ZHANG Laiping,DENG Xiaogang,ZHANG Hanxin.Reviews of moving grid generation techniques and numerical methods for unsteady flow[J].Advances in Mechanics,2010,40(4):424-447.(in Chinese)
[16]王卫星,郭荣伟.高超进气道自起动过程中流动非定常特性[J].航空学报,2015,36(10):3263-3274.WANG Weixing,GUO Rongwei.The unsteady flow characteristics of hypersonic inlet during self-starting[J].Acta Aeronautica et Astronautica Sinica,2015,36(10):3263-3274.(in Chinese)
[17]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)
[18]WANG Zhenguo,ZHAO Yilong,ZHAO Yuxin,et al.Prediction of massive separation of unstarted inlet via free-interaction theory[J].AIAA Journal,2015,53(4):1108-1112.
[19]陈卫明.二元高超声速进气道自起动特性的影响因素分析[D].南京:南京航空航天大学,2013.CHEN Weiming.Analysis of the influencing factors on two-dimensional hypersonic inlet self-starting characteristics[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2013.(in Chinese)
[20]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)
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