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Knowledge Management System of Institue of Mechanics, CAS
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Design methodology for shape transition inlets based on constant contraction of discrete streamtubes
期刊论文
PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING, 2016, 卷号: 230, 期号: 8, 页码: 1496-1506
Authors:
Xiao YB(肖雅斌)
;
Yue LJ(岳连捷)
;
Ma SH
;
Zhang XY(张新宇)
;
Yue, LJ (reprint author), Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, 15 Beisihuanxi Rd, Beijing 100864, Peoples R China.
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View/Download:431/101
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Submit date:2016/09/14
Hypersonic Inlet
Shape Transition
Inward Turning
Scramjet
Design Method
Engine performance analysis and optimization of a dual-mode scramjet with varied inlet conditions
期刊论文
ACTA MECHANICA SINICA, 2016, 卷号: 32, 期号: 1, 页码: 75-82
Authors:
Tian L
;
Chen LH(陈立红)
;
Chen Q(陈强)
;
Zhong FQ(仲峰泉)
;
Zhang XY(张新宇)
;
Chen, LH (reprint author), Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China.
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View/Download:346/88
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Submit date:2016/09/14
Dual-mode Scramjet
Engine Performance
Thrust
Optimization
Heat Release Distribution
Simulated Annealing Algorithm
Numerical study of combustion and convective heat transfer of a Mach 2.5 supersonic combustor
期刊论文
APPLIED THERMAL ENGINEERING, 2015, 卷号: 89, 页码: 883-896
Authors:
Wang X
;
Zhong FQ(仲峰泉)
;
Gu HB(顾宏斌)
;
Zhang XY(张新宇)
;
Zhong, FQ (reprint author), 15 Beisihuanxi Rd, Beijing 100190, Peoples R China.
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Submit date:2016/01/08
Supersonic Combustor
Convective Heat Transfer
Numerical Study
Wall Heat Flux
Experimental study on the effect of combustor configuration on the performance of dual-mode combustor
期刊论文
AEROSPACE SCIENCE AND TECHNOLOGY, 2015, 卷号: 42, 页码: 169-175
Authors:
Wang ZP(王知溥)
;
Li F(李飞)
;
Gu HS
;
Yu XL(余西龙)
;
Zhang XY(张新宇)
;
Li, F (reprint author), Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China.
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View/Download:557/231
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Submit date:2015/06/12
Scramjet
Dual-mode Combustor
Divergent Angle
Cavity Location
Combustion Efficiency
Tdlas
Numerical analysis on the heat transfer of three types of nozzles for the hypersonic long-run wind tunnel
期刊论文
Science China-Technological Sciences, 2015, 卷号: 58, 期号: 3, 页码: 470-475
Authors:
Xing YF(邢云绯)
;
Zhong FQ(仲峰泉)
;
Li DX(李东霞)
;
Zhang XY(张新宇)
;
Zhong, FQ (reprint author), Chinese Acad Sci, Inst Mech, Natl Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China.
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View/Download:454/196
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Submit date:2015/04/28
Hypersonic Scramjet Test Tunnel
Nozzle
Aerodynamic Heating
Convective Heat Transfer
Numerical Study of Turbulent Flow and Convective Heat Transfer Characteristics in Helical Rectangular Ducts
期刊论文
JOURNAL OF HEAT TRANSFER-TRANSACTIONS OF THE ASME, 2014, 卷号: 136, 期号: 12, 页码: 121701
Authors:
Xing YF(邢云绯)
;
Zhong FQ(仲峰泉)
;
Zhang XY(张新宇)
;
Zhong, FQ (reprint author), Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China.
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View/Download:329/75
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Submit date:2015/01/04
Helical Rectangular Duct
Heat Transfer
Turbulent Flow
Curvature
Torsion
Quasi-One-Dimensional Multimodes Analysis for Dual-Mode Scramjet
期刊论文
JOURNAL OF PROPULSION AND POWER, 2014, 卷号: 30, 期号: 6, 页码: 1559-1567
Authors:
Tian L
;
Chen LH(陈立红)
;
Chen Q(陈强)
;
Li F(李飞)
;
Zhang XY(张新宇)
;
Tian, L (reprint author), Chinese Acad Sci, State Key Lab High Temp Gas Dynam, Inst Mech, Beijing 100190, Peoples R China.
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View/Download:596/136
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Submit date:2014/12/18
Interaction of isentropic compression waves with a bow shock
期刊论文
AIAA JOURNAL, 2013, 卷号: 51, 期号: 10, 页码: 2474-2484
Authors:
Lu HB(卢洪波)
;
Yue LJ(岳连捷)
;
Xiao YB(肖雅彬)
;
Zhang XY(张新宇)
;
Yue, LJ (reprint author), Chinese Acad Sci, Inst Mech, State Key Lab High Temperature Gas Dynam, Beijing 100190, Peoples R China.
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Submit date:2014/01/17
Theoretical analysis of effects of boundary layer bleed on scramjet thrust
期刊论文
SCIENCE CHINA-PHYSICS MECHANICS & ASTRONOMY, 2013, 卷号: 56, 期号: 10, 页码: 1952-1961
Authors:
Yue LJ(岳连捷)
;
Xu XK(徐显坤)
;
Zhang XY(张新宇)
;
Yue, LJ (reprint author), Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China.
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Submit date:2013/10/23
Scramjet
Boundary Layer Bleed
Theoretical Analysis
Engine Thrust
Numerical simulation of ignition and combustion of ethylene in a supersonic model combustor with a reduced kinetic mechanism
期刊论文
COMBUSTION SCIENCE AND TECHNOLOGY, 2013, 卷号: 185, 期号: 4, 页码: 548-563
Authors:
Zhong FQ(仲峰泉)
;
Chen LH(陈立红)
;
Li F(李飞)
;
Zhang XY(张新宇)
;
Sung CJ
;
Zhong, FQ (reprint author), Chinese Acad Sci, State Key Lab High Temp Gas Dynam, Inst Mech, Beijing 100190, Peoples R China.
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View/Download:1432/487
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Submit date:2013/05/03
Ethylene
Ignition
Numerical Simulation
Reduced Kinetic Mechanism
Supersonic Combustion