高超声速进气道快速破膜开启的流动特性

doi:10.7527/S1000-6893.2014.0303

Abstract

Abstract:

Reliable in-flight starting of the hypersonic inlet is of critical importance for the successful operation of scramjet engines and taking the method of diaphragm rupture can effectively improve the inlet starting ability due to unsteady flow effect. In this paper, time-accurate computations have been performed to investigate the effects on inlet starting process at different diaphragm positions. The evolution process of the inlet flow pattern is analyzed and the mechanism of the separation bubble formation in the throat is thus elucidated. The results show that the unsteady reflected shock interacts with the interface and expansion waves to trigger a low-speed flow when no separation bubble occurs in front of the diaphragm. A separation bubble then forms in the inlet throat, resulting from the low-speed flow under the interaction of cowl shock. Installing the diaphragm downstream would improve the inlet starting ability by decreasing the low-speed flow area. When large separation bubble occurs in front of the diaphragm, the separation bubble will first evolve to a low-speed flow after diaphragm rupture then develop to a new separation in the throat. The inlet starting ability degrades significantly.

Key words: hypersonic inlet, diaphragm rupture, unsteady flow effect, shock wave/boundary layer interaction, separation flow

CLC Number:

V214.8

XU Xiao, YUE Lianjie, LU Hongbo, XIAO Yabin, ZHANG Xinyu. Flow characteristics of hypersonic inlet starting with diaphragm rupture[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(6): 1795-1804.

References

[1] Hagenmaier M A, Tam C J, Chakravarthy S. Study of moving start door flow physics for scramjet, AIAA-1999-4957[R]. Reston: AIAA, 1999.
[2] Huebner L D, Rock K E, Ruf E G, et al. Hyper-X flight engine ground testing for X-43 flight risk reduction, AIAA-2001-1809[R]. Reston: AIAA, 2001.
[3] Grainger A L, Boyce R R, Tirtey S C, et al. The unsteady flow physics of hypersonic inlet starting processes, AIAA-2012-5937[R]. Reston: AIAA, 2012.
[4] Ogawa H, Grainger A L, Boyce R R. Inlet starting of high-contraction axisymmetric scramjets[J]. Journal of Propulsion and Power, 2011, 26(26): 1247-1258.
[5] Zhang L, Zhang K Y, Jin Z G, et al. Numerical simulation of a variable geometry designed with compressible ramp movable[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(10): 1800-1808 (in Chinese). 张林, 张堃元, 金志光, 等.高超声速二元进气道顶板移动变几何方案数值模拟[J]. 航空学报, 2012, 33(10): 1800-1808.
[6] Wang Y, Fan X Q, Liang J H, et al. Experimental investigation on the starting characteristics of a hypersonic inlet with moving entrance door[J]. Journal of Aerospace Power, 2008, 23(6): 1014-1018 (in Chinese). 王翼, 范晓樯, 梁剑寒, 等. 开启式高超声速进气道启动性能试验[J]. 航空动力学报, 2008, 23(6): 1014-1018.
[7] Tahir R B, Molder S. Unsteady starting of high Mach number air inlets-A CFD study, AIAA-2003-5191[R]. Reston: AIAA, 2003.
[8] Timofeev E V, Tahir R B, Molder S. On recent developments related to flow starting in hypersonic air intakes, AIAA-2008-2512[R]. Reston: AIAA, 2008.
[9] 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.
[10] Clemens N T, Narayanaswamy V. Low-frequency unsteadiness of shock wave/turbulent boundary layer interactions[J]. Annual Review of Fluid Mechanics, 2013, 46: 469-492.
[11] Liang D W, Yuan H C, Zhang X J. Research on the effects of start ability of hypersonic inlet[J]. Journal of Astronautics, 2006, 27(4): 714-719 (in Chinese). 梁德旺, 袁化成, 张晓嘉. 影响高超声速进气道起动能力的因素分析[J]. 宇航学报, 2006, 27(4): 714-719.
[12] Holger B, Harvey J K. Shock wave boundary-layer interactions[M]. Cambridge, UK: Cambridge University Press, 2011: 141-159.
[13] Loth E, Titchener N, Babinsky H, et al. Canonical normal shock wave/boundary-layer interaction flows relevant to external compression inlets[J]. AIAA Journal, 2013, 51(9): 2208-2217.
[14] Zhang X J, Yue L J, Chang X Y. Shock arrangement of ramp compression hypersonic inlet with high internal contraction ratio[J]. Journal of Propulsion Technology, 2012, 33(4): 505-509 (in Chinese) 张晓嘉, 岳连捷, 张新宇. 大内收缩比二元高超声速进气道波系配置特性[J]. 推进技术, 2012, 33(4): 505-509.
[15] Yue L J, Zhang X J, Chen L H, et al. Reaserch on optimal design methodology on 2D hypersonic inlet, CSTAM 2008-0028[R]. [s.l.]: CSTAM, 2008. 岳连捷, 张晓嘉, 陈立红, 等. 二元高超声速进气道优化设计方法研究, CSTAM 2008-0028[R]. [s.l.]: CSTAM, 2008.
[16] Korkegi R H. Compression of shock induced two- and three-dimensional incipient turbulence separation[J]. AIAA Journal, 1975, 13(4): 534-535.
[17] Boyce R R, Gerard S, Paull A. The HyShot scramjet flight experiment—flight data and CFD calculations compared, AIAA-2003-7029[R]. Reston: AIAA, 2003.
[18] Boyce R R, Hillier R. Shock-induced three-dimensional separation of an axisymmetric hypersonic turbulent boundary layer, AIAA-2000-2226[R]. Reston: AIAA, 2000.
[19] Lu H B, Yue L J, Xiao Y B, et al. Interaction of isentropic compression waves with a bow shock[J]. AIAA Journal, 2013, 51(10): 2208-2217.
[20] Lu H B, Yue L J, Chang X Y. Flow characteristics of hypersonic inlets with different cowl-lip blunting methods[J]. Science China Physics, Mechanics and Astronomy, 2014, 57(4): 741-752.
[21] van Wie D M, Kwok F T, Walsh R F. Starting characteristics of supersonic inlets, AIAA-1996-2914[R]. Reston: AIAA, 1996.

Flow characteristics of hypersonic inlet starting with diaphragm rupture

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 15

Recommended Articles

Metrics

Comments

[1]	Jiang LAI, Zhaolin FAN, Qian WANG, Siwei DONG, Fulin TONG, Xianxu YUAN. Direct numerical simulation of hypersonic cone-flare model at angle of attack [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(2): 128610-128610.
[2]	Li NONG, Zishuai SHENG, Jun XIAN, Huaibao ZHANG. Numerical simulation of separated flow around iced airfoil based on high⁃order schemes [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(S2): 729291-729291.
[3]	Weijia LIU, Yingkun LI, Xiong CHEN, Chunlei LI. Panel flutter characteristics on shock wave/boundary layer interaction based on fluid⁃structure coupling [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(6): 127085-127085.
[4]	Mengge WANG, Xiaoming HE, Juanjuan WANG, Yue ZHANG, Kun WANG, Huijun TAN, Liugang LI. Shock wave/boundary layer interaction control method based on oscillating vortex generator [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(20): 128503-128503.
[5]	Shanshan TIAN, Liang JIN, Zhaobo DU, Xiangyu ZHONG, Wei HUANG, Yuanyang LIU. Research progress of shock wave/boundary layer interaction controls induced by bump [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(18): 28411-028411.
[6]	Zhenbing LUO, Wei XIE, Xuzhen XIE, Yan ZHOU, Qiang LIU. Research progress of active flow control of shock wave and its interaction [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(15): 529002-529002.
[7]	Yongzhou LI, Di SUN, Renhua WANG, Kunyuan ZHANG. Design of inward turning inlet with controlled Mach number under non-uniform inflow [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(12): 127857-127857.
[8]	Yatian ZHAO, Zhiyuan SHAO, Chao YAN, Xinghao XIANG. Comparative analysis of Reynolds stress and eddy viscosity models in separation flow prediction [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(11): 127619-127619.
[9]	CHENG Jianrui, SHI Chongguang, QU Lixia, XU Yue, YOU Yancheng, ZHU Chengxiang. Theoretical model of 2D curved shock wave/turbulent boundary layer interaction [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(9): 125993-125993.
[10]	WANG Yi, XU Shangcheng, ZHOU Yunfan, FAN Xiaoqiang, WANG Zhenguo. Multi-objective design and analysis of cowl lip angle for hypersonic inlet [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(8): 125698-125698.
[11]	ZHANG Haoyuan, SUN Dong, QIU Bo, ZHU Yandan, WANG Anling. Influence of turbulent kinetic energy on shock wave/boundary layer interaction [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(7): 125504-125504.
[12]	WEI Ziyan, LI Jie, ZHANG Heng, YANG Zhao. Improved aerodynamic design of laminar wing section of laminar verifying aircraft [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(11): 526760-526760.
[13]	WANG Hongyu, YANG Yanguang, HU Weibo, CHEN Zhi, FENG Liming, ZHOU Youtian. Experimental study on unsteadiness characteristics of shock wave/turbulent boundary layer interaction controlled by high-frequency microsecond pulse discharge [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 625905-625905.
[14]	SHEN Pengfei, LIU Pengxin, SUN Dong, YUAN Xianxu. Statistical characteristics of skin friction of shock wave/turbulent boundary layer interaction in hollow cylinder-flare configuration at Mach 6 [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 626005-626005.
[15]	GANG Dundian, YI Shihe, MI Qi, NIU Haibo. Experiment on interaction between supersonic turbulent boundary layer and cylinder [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 626104-626104.