方转圆对三维侧压进气道的流动特性影响

doi:10.7527/S1000-6893.2014.0172

Abstract

Abstract:

The effect of rectangular-to-circular on the performance and flow field of three-dimensional sidewall compression hypersonic inlet is investigated in this article. The basic performance and flow field of the original inlet with rectangular outlet, the inlet rounding from throat, and the inlet rounding from the front of sidewall root, are compared with each other through numerical simulation. The results reveal that the gross performance of inlets with rectangular-to-circular isolator are better than the original inlet, and in the two rectangular-to-circular inlets, Scheme 3 that takes the internal converging portion and isolator as a whole is superior to Scheme 2 that rounding from throat, the common characteristics of secondary flow in the isolator of the three schemes is that nearby the bottom wall exist two opposite flow-directional vortices, and the relationship between them determines the distribution and development of the bottom low-energy flow region, rectangular-to-circular process from the front of side wall root has a stronger enhancement on the side wall vortex than that from throat, which produces the roll-down effect so that it can improve the corner low-energy flow.

Key words: rectangular-to-circular, hypersonic, three-dimensional sidewall compression, inlet, internal contraction duct, isolator

CLC Number:

V211

LIU Xiong, WANG Yi, LIANG Jianhan. Effect of Rectangular-to-circular on Flow Characteristics of Three-dimensional Sidewall Compression Inlet[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(11): 2939-2948.

References

[1] Trexler C A. Performance of an inlet for an integrated scramjet concept[J]. Journal of Aircraft, 1974, 11(9): 589-591.

[2] Holland S D. Mach 10 experimental database of a three-dimensional scramjet inlet flow field, NASA TM 4686[R]. Washington, D.C.: NASA, 1995.

[3] Rodi P E, Trexler C A. The effect of bodyside compression on forward and aft swept sidewall compression inlets at Mach 4, AIAA-1994-2708[R]. Reston: AIAA, 1994.

[4] Panaras A G. Review of the physics of swept-shock/ boundary layer interactions[J]. Progress of Aerospace Science, 1996, 32(2): 173-244.

[5] Kiersey J L, Snow M L. Modular inlet investigation, Report AQR/66-1[R]. Baltimore: Aeronautics Div. Research and Development, Applied Physics Lab., Johns Hopkins University, 1966.

[6] Molder S, Romeskie J M. Modular hypersonic inlets with conical flow, AGARD CP-30[R]. Montreal: McGill University, 1968.

[7] Smart M K. Design of three-dimensional hypersonic inlet with rectangular to elliptical shape transition, AIAA-1998-0960[R]. Reston: AIAA, 1998.

[8] Smart M K. Experimental testing of a hypersonic inlet with rectangular-to elliptical shape transition, AIAA-1999-0085[R]. Reston: AIAA, 1999.

[9] Smart M K, White J A. Computational investigation of the performance and back-pressure limits of a hypersonic inlet, AIAA-2002-0508[R]. Reston: AIAA, 2002.

[10] Smart M K, Trexler C A. Mach 4 performance of hypersonic inlet with rectangular-to-elliptical shape transition[J]. Journal of Propulsion and Power, 2004, 20(2): 288-293.

[11] Smart M K, Ruf E G. Free-jet testing of a REST scramjet at off-design conditions, AIAA-2006-2955[R]. Reston: AIAA, 2006.

[12] Gollan R J. Design of modular, shape-transitioning inlets for a conical hypersonic vehicle[C]//48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, 2010.

[13] Taylor T M. Performance analysis of hypersonic shape-changing inlets derived from morphing streamline traced flowpaths, AIAA-2008-2635[R]. Reston: AIAA, 2008.

[14] Gollan R J. Investigation of REST-class hypersonic inlet designs, AIAA-2011-2254[R]. Reston: AIAA, 2011.

[15] Ferlemann P G, Gollan R J. Parametric geometry, structured grid generation, and initial design study for REST-class hypersonic inlets[C]//Jannaf Airbreathing Propulsion Subcommittee Meeting, 2009.

[16] Nan X J, Zhang K Y, Jing Z G, et al. Numerical and experimental investigation of hypersonic inward turning inlets with rectangular to circular shape transition[J]. Acta Aeronautica et Astronautica Sinica, 2011, 32(6): 988-996. (in Chinese) 南向军, 张堃元, 金志光, 等. 矩形转圆形高超声速内收缩进气道数值及试验研究[J].航空学报, 2011, 32(6): 988-996.

[17] Nan X J, Zhang K Y, Jing Z G. Experimental study of hypersonic inward turning inlets with innovative basic flowfield[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(1): 90-96.(in Chinese) 南向军, 张堃元, 金志光. 采用新型基准流场的高超内收缩进气道试验研究[J].航空学报, 2014, 35(1): 90-96.

[18] Fluent Inc. FLUENT user's guide[M]. Pittsburgh: Fluent Inc., 2003.

[19] Moin P. Progress in large eddy simulation of turbulence flows, AIAA-1997-15761[R]. Reston: AIAA, 1997.

[20] Wang Y. Investigation on the starting characteristics of hypersonic inlet[D]. Changsha: National University of Defense Technology, 2008. (in Chinese) 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.

Effect of Rectangular-to-circular on Flow Characteristics of Three-dimensional Sidewall Compression Inlet

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 15

Recommended Articles

Metrics

Comments

[1]	Zeyong YIN, Yancheng YOU, Chengxiang ZHU, Jianfeng ZHU, Liaoni WU, Yue HUANG. Multi-ducted twin-turbines ejector-ramjet/scramjet combined cycle engine for hypersonic civil vehicles [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(2): 627181-627181.
[2]	Zhikun SUN, Zhiwei SHI, Weilin ZHANG, Zheng LI, Qijie SUN. Effect of plasma actuator on lift-drag characteristics of high-speed airfoil [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 23-39.
[3]	Weizhuo HUA, Ling GAO, Ge CHEN, Yiwen LI, Geng GONG, Yantao WANG, Biao WEI. Experimental magneto-hydrodynamic system based on plasma torch [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 1-7.
[4]	Yifeng HUANG, Shuhua ZENG, Zhongzheng JIANG, Weifang CHEN. Numerical study on high-altitude lateral jet based on nonlinear coupled constitutive relation [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 8-22.
[5]	Kai LUO, Yonghai WANG, Qiu WANG, Jiwei LI, Zheng LI, Chunsheng NIE, Zheng LI. Plasma-actuated flow control test in high enthalpy shock tunnel [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 89-96.
[6]	Xudong ZHANG, Zheng LI, Hao DONG, Siyuan GAO, Zubi JI, Kaixin LI, Guanghui BAI. Drag reduction characteristics of opposing plasma synthetic jet in hypersonic flow [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 115-123.
[7]	Shouchao HU, Yu ZHUANG, Xian LI, Tao JIANG. Hypersonic aero-heating environment research model HyHERM-I: Experiment [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 233-248.
[8]	Haoge LI, Hua YANG, Yuxin YANG, Weifang CHEN. Refinement optimization design for heat reduction on windward surface of hypersonic lifting body [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 124-137.
[9]	Dong WU, Hong YANG, Wenfeng ZHAO, Yue LUO. High temperature strain measurement of hypersonic aircraft carbon-based composite material structures [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 160-169.
[10]	Chunsheng NIE, Ye YUAN, Wei MA, Zhanwei CAO, Mingxing YU. Effect of active ejection gas parameters on thermal environment of plate and air rudder [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 170-179.
[11]	Zhengxue MA, Zhenbing LUO, Aihong ZHAO, Yan ZHOU, Wei XIE, Qiang LIU, Yinxin ZHU, Wenqiang PENG. Reverse jet characteristics of plasma synthetic jet in hypersonic flow field [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 192-203.
[12]	LI Jun, WANG Junfeng, ZHAO Yatian, LUO Shibin. Research on combinational configuration of spike and multi-jets in off-design regimes [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(9): 125949-125949.
[13]	LIU Chuanzhen, MENG Xufei, LIU Rongjian, BAI Peng. Experimental and numerical investigation of hypersonic performance of double swept waverider [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(9): 126015-126015.
[14]	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.
[15]	LIU Qingyang, LEI Juanmian, LIU Zhou, SHI Lei, ZHOU Weijiang. γ-Re_θt-f_Re transition model for compressible flow [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(8): 125794-125794.