An analysis on typical influencing factors of wind tunnel experimental model of over-under TBCC inlet mode transition

Liu Yuan; Qian Zhansen; Xiang Xianhong

doi:10.11729/syltlx20190007

Volume 33 Issue 5

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Liu Yuan, Qian Zhansen, Xiang Xianhong. An analysis on typical influencing factors of wind tunnel experimental model of over-under TBCC inlet mode transition[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(5): 18-27. doi: 10.11729/syltlx20190007

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An analysis on typical influencing factors of wind tunnel experimental model of over-under TBCC inlet mode transition

doi: 10.11729/syltlx20190007

Liu Yuan^{1, 2
,},
Qian Zhansen^{1, 2
,
,},
Xiang Xianhong^{1, 2}

1.
AVIC Aerodynamics Research Institude, Shenyang 110034, China
2.
Aviation Key Laboratory of Science and Technology on High Speed and High Reynolds Number Aerodynamic Force Research, Shenyang 110034, China

Received Date: 2019-01-03
Rev Recd Date: 2019-09-04
Publish Date: 2019-10-25

Abstract

Abstract

The aerodynamic performance of a typical over-under TBCC inlet mode transition model has been studied by wind tunnel experiments, and the CFD methods used have also been verified. In the present work, the influence of three typical factors on the experiment is studied by the CFD method, including the side gap, the leading edge bluntness and the forward step on the inner surface. The research results show that the gap between the splitter and the side plate leads to flow spillage between the high and low speed channels. When the gap width reaches 0.5 mm, the total pressure recovery coefficient of the high speed channel is increased by 2.13%, while the flow coefficient is improved by 2.27%. This already has an impact on the aerodynamic performance evaluation of the inlet so that the gap of the model plate should be less than 0.5 mm.The blunted radius of the leading edge has little influence on the aerodynamic performance of the inlet. For the general machining accuracy (0.3 mm), the inlet performance remains basically unchanged. For the general assembly accuracy (0.5 mm), the forward step has very little influence on the inlet flow coefficient, and the total pressure recovery coefficient of the inlet is decreased by 0.44%, which can satisfy the requirements of aerodynamic performance evaluation of the TBCC inlet.
- TBCC inlet,
- wind tunnel experimental model,
- side gap,
- leading edge bluntness,
- upwind step

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References(13)

References

[1]	Thomas S R. TBCC discipline overview. Hypersonics project[C]//Proc of the 2011 Technical Conference. 2011.
[2]	乐嘉陵, 胡欲立, 刘陵.双模态超燃冲压发动机研究进展[J].流体力学实验与测量, 2000, 14(1):1-12. doi: 10.3969/j.issn.1672-9897.2000.01.001 Le J L, Hu Y L, Liu L. Investigation of possibilities in developing dual mode scramjets[J]. Experiments and Measurements in Fluid Mechanics, 2000, 14(1):1-12. doi: 10.3969/j.issn.1672-9897.2000.01.001
[3]	Cockrell C E, Auslender A H, Guy R W, et al. Technology roadmap for dual-mode scramjet propulsion to support space-access vision vehicle development[R]. AIAA 2002-5188, 2002.
[4]	张华军, 郭荣伟, 李博. TBCC进气道研究现状及其关键技术[J].空气动力学学报, 2010, 28(5):613-620. doi: 10.3969/j.issn.0258-1825.2010.05.022 Zhang H J, Guo R W, Li B. Research status of TBCC inlet and its key technologies[J]. Acta Aerodynamica Sinica, 2010, 28(5):613-620. doi: 10.3969/j.issn.0258-1825.2010.05.022
[5]	向先宏, 钱战森, 张铁军. TBCC进气道模态转换气动技术研究综述[J].航空科学技术, 2017, 28(1):10-18. http://d.old.wanfangdata.com.cn/Periodical/hkkxjs201701002 Xiang X H, Qian Z S, Zhang T J. An overview of Turbine-Based Combined cycle (TBCC) inlet mode transition aerodynamic technology[J]. Aeronautical Science and Technology, 2017, 28(1):10-18. http://d.old.wanfangdata.com.cn/Periodical/hkkxjs201701002
[6]	Albertson C W, Emani S, Trexler C A. Mach 4 test results of a dual-flowpath turbine based combined cycle inlet[R]. AIAA 2006-8138, 2006.
[7]	Sanders B W, Weir L J. Aerodynamic design of a dual-flow Mach 7 hypersonic inlet system for a turbine-based combined-cycle hypersonic propulsion system[R]. NASA/CR-2008-215214, 2008.
[8]	Saunders J D, Slater J W, Dippold V, Lee J, et al. Inlet mode transition screening test for a turbine-based combined-cycle propulsion system[C]//Proc of the 55th JANNAF Propulsion Meeting. 2008.
[9]	蔡元虎, 张建东, 王占学. TBCC发动机用进气道设计及沿飞行轨迹斜板角度优化分析[J].西北工业大学学报, 2007, 25(5):615-619. doi: 10.3969/j.issn.1000-2758.2007.05.001 Cai Y H, Zhang J D, Wang Z X. Exploring TBCC engine inlet design and along the flight path angle optimization analysis[J]. Journal of Northwestern Polytechnical University, 2007, 25(5):615-619. doi: 10.3969/j.issn.1000-2758.2007.05.001
[10]	Chen M, Tang H L, Zhu Z L, et al. Inlet/TBCC/Nozzle integration concept design[R]. AIAA 2008-4588, 2008.
[11]	李龙, 李博, 梁德旺, 等.涡轮基组合循环发动机并联式进气道的气动特性[J].推进技术, 2008, 29(6):667-672. doi: 10.3321/j.issn:1001-4055.2008.06.006 Li L, Li B, Liang D W, et al. Aerodynamic characteristics of over/under inlet for turbine based combined cycle engine[J]. Journal of Propulsion Technology, 2008, 29(6):667-672. doi: 10.3321/j.issn:1001-4055.2008.06.006
[12]	Xiang X H, Liu Y, Qian Z S. Aerodynamic design and numerical simulation of over-under turbine-based combined-cycle (TBCC) inlet mode transition[J]. Procedia Engineering, 2015, 99:129-136. doi: 10.1016/j.proeng.2014.12.516
[13]	Liu Y, Wang L, Qian Z S. Numerical investigation on the assistant restarting method of variable geometry for high Mach number inlet[J]. Aerospace Science and Technology, 2018, 79:647-657. doi: 10.1016/j.ast.2018.06.014