| Citation: | JIN Yichao, YAN Chao, LIN Boxiet al. Effect of injection on starting characteristics of hypersonic inlet[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(11): 2302-2309. doi: 10.13700/j.bh.1001-5965.2017.0191(in Chinese)
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In order to explore the feasibility of using injection technology to reduce the start Mach number of hypersonic inlet, the flow field of the two-dimensional hypersonic inlet was calculated by numerical simulation. The effect of injection on the hypersonic inlet was analyzed by comparing the flow field structure, mass-captured coefficient and total pressure recovery coefficient under different working conditions, and the influence of jet velocity, pressure and angle of inclination on starting performance of the inlet was also studied. The analysis results show that the change of original interference form of the shock wave and inlet boundary-layer is the main reason for the reduction of the start Mach number of inlet. The study also shows that increasing jet velocity is conducive to improving the control effect, but increasing jet velocity continuously would result in an increase in the back pressure of the isolation section. This phenomenon is related to the jet pressure, and reducing the jet pressure could expand the effective jet velocity range to start the inlet. At different jet angles of inclination, the above rules are consistent. The simulation results reveal the systematic rule of changes of the inlet starting ability with injection parameters, which can be used to guide engineering design and optimization.
| [1] |
HABERLE J, GULHAN A.Investigation of the performance of a scramjet inlet at Mach 6 with boundary layer bleed:AIAA-2006-8139[R].Reston:AIAA, 2006. doi: 10.2514/6.2006-8139
|
| [2] |
SMART M K, TREXLER C A.Mach 4 performance of hypersonic inlet with rectangular-to-elliptical shape transition[J].Journal of Propulsion and Powder, 2004, 20(2):288-293. doi: 10.2514/1.1296
|
| [3] |
WHITE M E, LEE R E, THOMPSON M W, et al.Tangential mass addition for shock/boundary-layer interaction control in scramjet inlets[J].Journal of Propulsion, 1991, 7(6):1023-1029. doi: 10.2514/3.23422
|
| [4] |
ROZARIO D, ZOUAOUI Z.Computational fluid dynamic analysis of scramjet inlet:AIAA-2007-0030[R].Reston:AIAA, 2007.
|
| [5] |
BITYURIN V A, BOCHAROV A N, LINEBERRY J T, et al.Experimental and theoretical study of MHD interaction in hypersonic ionized air flow over a wedge:AIAA-2004-1194[R].Reston:AIAA, 2004. doi: 10.2514/6.2004-1194
|
| [6] |
SHEIKIN E G, KURANOW A L.MHD control in hypersonic aircraft:AIAA-2005-1335[R].Reston:AIAA, 2005.
|
| [7] |
GORTON S, OWENS L, JENKINS L, et al.Active flow control on a boundary-layer-ingesting inlet:AIAA-2004-1203[R].Reston:AIAA, 2004.
|
| [8] |
ALLAN B, OWEN L, BERRIER B.Numerical modeling of active flow control in a boundary layer ingesting offset inlet:AIAA-2004-2318[R].Reston:AIAA, 2004.
|
| [9] |
VAN WIE D M, KWOK F T, WALSH R T.Starting characteristics of supersonic inlets:AIAA-1996-2914[R].Reston:AIAA, 1996.
|
| [10] |
FENG X P, LIN Z Y, ZHENG Y, et al.Adjusting principle of gas jet controlling inlet and numerical verification[J].Science China Technological Sciences, 2011, 54(11):2981-2986. doi: 10.1007/s11431-011-4553-3
|
| [11] |
方传波, 夏智勋, 胡建新, 等.基于主动射流控制的二元混压式进气道起动特性研究[J].固体火箭技术, 2010, 33(3):280-284.
FANG C B, XIA Z X, HU J X, et al.Study on starting characteristics of a two-dimensional supersonic inlet based on actve injection control[J].Journal of Solid Rocket Technology, 2010, 33(3):280-284(in Chinese).
|
| [12] |
EMAMI S, TREXLER C A, AUSLENDER A H, et al.Experimental investigation of inlet-combustor isolators for a dual-mode scramjet at a Mach number of 4:NASA Technical Paper 3502[R].Washington, D.C.:NASA, 1995.
|
| [13] |
林博希, 阎超, 李亚超.喷流干扰气动热数值模拟的若干影响因素[J].北京航空航天大学学报, 2016, 42(6):1210-1218.
LIN B X, YAN C, LI Y C.Some influence factors in aerodynamic heat transfer numerical simulation of jet-interaction flow[J].Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(6):1210-1218(in Chinese).
|
| [14] |
PATRICK E R, EMAMI S, CARL A T.Unsteady pressure behavior in a ramjet/scramjet inlet[J].Journal of Propulsion and Power, 1996, 12(3):486-493. doi: 10.2514/3.24061
|
| [15] |
COX C, LEWIS C, PAP R.Prediction of unstart phenomena in hypersonic aircraft:AIAA-1995-6018[R].Reston:AIAA, 1995.
|
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