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On-line Access: 2022-06-24

Received: 2021-10-21

Revision Accepted: 2022-01-04

Crosschecked: 2022-06-24

Cited: 0

Clicked: 334

Citations:  Bibtex RefMan EndNote GB/T7714

 ORCID:

Shang-cheng XU

https://orcid.org/0000-0002-0717-8392

Yi WANG

https://orcid.org/0000-0002-3657-9769

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Journal of Zhejiang University SCIENCE A 2022 Vol.23 No.6 P.479-494

http://doi.org/10.1631/jzus.A2100532


Design method for hypersonic bump inlet based on transverse pressure gradient


Author(s):  Shang-cheng XU, Yi WANG, Zhen-guo WANG, Xiao-qiang FAN, Bing XIONG

Affiliation(s):  College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China

Corresponding email(s):   wange_nudt@163.com

Key Words:  Hypersonic bump inlet, Transverse pressure gradient (TPG), Boundary layer flow, Total pressure recovery, Starting ability, Mass flow correction


Shang-cheng XU, Yi WANG, Zhen-guo WANG, Xiao-qiang FAN, Bing XIONG. Design method for hypersonic bump inlet based on transverse pressure gradient[J]. Journal of Zhejiang University Science A, 2022, 23(6): 479-494.

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author="Shang-cheng XU, Yi WANG, Zhen-guo WANG, Xiao-qiang FAN, Bing XIONG",
journal="Journal of Zhejiang University Science A",
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pages="479-494",
year="2022",
publisher="Zhejiang University Press & Springer",
doi="10.1631/jzus.A2100532"
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%A Yi WANG
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DOI - 10.1631/jzus.A2100532


Abstract: 
transverse pressure gradient (TPG) is one of the key factors influencing the boundary layer airflow diversion in a bump inlet. This paper proposes a novel TPG-based hypersonic bump inlet design method. This method consists of two steps. First, a parametric optimization approach is employed to design a series of 2D inlets with various compression efficiencies. Then, according to the prescribed TPG, the optimized inlets are placed in different osculating planes to generate a 3D bump inlet. This method provides a means to directly control the aerodynamic parameters of the bump rather than the geometric parameters. By performing this method to a hypersonic chin inlet, a long and wide bump surface is formed in the compression wall, which leads to good integration of the bump/inlet. Results show that a part of the near-wall boundary layer flow is diverted by the bump, resulting in a slight decrease in the mass flow but a significant improvement in the total pressure recovery. In addition, the starting ability is significantly improved by adding the bump surface. Analysis reveals that the bump has a 3D rebuilding effect on the large-scale separation bubble of the unstarted inlet. Finally, a mass flow correction is performed on the designed bump inlet to increase the mass flow to full airflow capture. The results show that the mass flow rate of the corrected bump inlet reaches up to 0.9993, demonstrating that the correction method is effective.

基于横向压力梯度的高超声速鼓包进气道设计方法

作者:徐尚成,王翼,王振国,范晓樯,熊冰
机构:国防科技大学,空天科学学院,中国长沙,410073
目的:在超/高超声速进气道中,横向压力梯度是鼓包对边界层气流产生排移的关键,然而目前基于横向压力梯度的鼓包设计方法还有待进一步发展。本文旨在提出一种横向压力梯度驱动的高超声速鼓包进气道设计方法,以实现鼓包型面上横向压力梯度完全可控。在此基础上分析鼓包对进气道性能的影响,并从流动层面解释其原因。
创新点:1.提出了一种由横向压力梯度驱动的高超声速鼓包进气道设计方法,实现了鼓包与进气道完全一体化的设计;2.明晰了鼓包型面对不起动进气道大尺度分离区的三维重构作用,进而解释了鼓包进气道起动性能改善的原因。
方法:1.通过对鼓包工作原理的分析,提出一种基于横向压力梯度的高超声速鼓包进气道设计方法;2.通过数值仿真,研究鼓包进气道在设计点下对边界层气流的排移效果(图14);3.通过数值仿真和风洞实验相结合的方法,研究鼓包对不起动进气道大尺度分离区的三维重构作用,进而分析鼓包对进气道起动过程的作用机理。
结论:1.采用本文提出的方法实现了由横向压力梯度驱动的鼓包型面设计,且该型面与进气道外压缩面完全一体化;2.在横向压力梯度的作用下,一部分边界层气流被排移出进气道,使得进气道流量系数稍有下降,但总压恢复性能明显提高;3.鼓包型面对不起动状态下的进气道大尺度分离区具有三维重构作用,使得进气道起动性能得到提高;4.采用本文提出的流量修正方法可使鼓包进气道实现全流量捕获。

关键词:高超声速鼓包进气道;横向压力梯度;边界层气流;总压恢复;起动性能;流量修正

Darkslateblue:Affiliate; Royal Blue:Author; Turquoise:Article

Reference

[1]BhanderiH, BabinskyH, 2005. Improved boundary layer quantities in the shock wave boundary layer interaction region on bumps. Proceedings of the 35th AIAA Fluid Dynamics Conference and Exhibit.

[2]ChengSX, ZhanH, ShuZX, et al., 2019. Effective optimization on bump inlet using meta-model multi-objective particle swarm assisted by expected hyper-volume improvement. Aerospace Science and Technology, 87:431-447.

[3]CollissSP, BabinskyH, NüblerK, et al., 2014. Joint experimental and numerical approach to three-dimensional shock control bump research. AIAA Journal, 52(2):436-446.

[4]CurranET, 2001. Scramjet engines: the first forty years. Journal of Propulsion and Power, 17(6):1138-1148.

[5]CurranET, MurthySNB, 2001. Scramjet Propulsion. American Institute of Aeronautics and Astronautics, Reston, USA, p.462-466.

[6]DingF, LiuJ, ShenCB, et al., 2018. An overview of waverider design concept in airframe/inlet integration methodology for air-breathing hypersonic vehicles. Acta Astronautica, 152:639-656.

[7]GuoST, LiZF, GaoWZ, et al., 2017. Analogy between effects of attack angle and Mach number on inlet starting. Journal of Propulsion Technology, 38(5):983-991 (in Chinese).

[8]HuangGP, ZuoFY, QiaoWY, 2018. Design method of internal waverider inlet under non-uniform upstream for inlet/forebody integration. Aerospace Science and Technology, 74:160-172.

[9]HuangW, ChangJT, YanL, 2020. Mixing and combustion in supersonic/hypersonic flows. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 21(8):609-613.

[10]ImSK, DoH, 2018. Unstart phenomena induced by flow choking in scramjet inlet-isolators. Progress in Aerospace Sciences, 97:1-21.

[11]JohnsonCB, LawingPL, 1977. Mach 6 flowfield survey at the engine inlet of a research airplane. Journal of Aircraft, 14(4):412-414.

[12]KimJ, SungHJ, 2006. Wall pressure fluctuations in a turbulent boundary layer over a bump. AIAA Journal, 44(7):1393-1401.

[13]KimSD, 2009. Aerodynamic design of a supersonic inlet with a parametric bump. Journal of Aircraft, 46(1):198-202.

[14]KimSD, SongDJ, 2007. A numerical analysis on three-dimensional flow field in a supersonic bump-type inlet. Journal of Mechanical Science and Technology, 21(2):327-335.

[15]KimSD, SongDJ, 2008. Numerical study on performance of supersonic inlets with various three-dimensional bumps. Journal of Mechanical Science and Technology, 22(8):1640-1647.

[16]LauKY, 2008. Hypersonic boundary-layer transition: application to high-speed vehicle design. Journal of Spacecraft and Rockets, 45(2):176-183.

[17]LawingPL, JohnsonCB, 1978. Inlet boundary-layer shapes on four aircraft forebodies at Mach 6. Journal of Aircraft, 15(1):62-63.

[18]LiYQ, ZhengXG, ShiCG, et al., 2020. Integration of inward-turning inlet with airframe based on dual-waverider concept. Aerospace Science and Technology, 107:106266.

[19]LiuJB, FanXQ, TaoY, et al., 2019. Experimental and numerical study on the local unstart mechanism of hypersonic inlet. Acta Astronautica, 160:216-221.

[20]LoKH, KontisK, 2017. Flow characteristics of various three-dimensional rounded contour bumps in a Mach 1.3 freestream. Experimental Thermal and Fluid Science, 80:228-243.

[21]SahebyEB, HuangGP, QiaoWY, et al., 2016. Highly integrated inlet design based on the ridge concept. Journal of Propulsion and Power, 32(6):1505-1515.

[22]SahebyEB, HuangGP, HaysA, 2017. Design of hypersonic forebody by the combination of bump and waverider surfaces. Proceedings of the 21st AIAA International Space Planes and Hypersonics Technologies Conference.

[23]SchwartzMJ, GaitondeD, SlaterJ, 2021. Effects of bleed on supersonic turbulent boundary layers. Proceedings of the AIAA Aviation Forum.

[24]SimonPC, BrownDW, HuffRG, 1957. Performance of External-Compression Bump Inlet at Mach Numbers of 1.5 and 2.0. Report No. NACA-RM-E56L19, National Advisory Committee for Aeronautics, USA.

[25]SuWY, ChenY, ZhangFR, et al., 2018. Control of pseudo-shock oscillation in scramjet inlet-isolator using periodical excitation. Acta Astronautica, 143:147-154.

[26]SvenssonM, 2008. A CFD Investigation of a Generic Bump and Its Application to a Diverterless Supersonic Inlet. MS Thesis, Linköping University, Linköping, Sweden.

[27]SziroczakD, SmithH, 2016. A review of design issues specific to hypersonic flight vehicles. Progress in Aerospace Sciences, 84:1-28.

[28]TillotsonBJ, LothE, DuttonJC, et al., 2009. Experimental study of a Mach 3 bump-compression flowfield. Journal of Propulsion and Power, 25(3):545-554.

[29]TrefnyCJ, 1999. An air-breathing launch vehicle concept for single-stage-to-orbit. Proceedings of the 35th Joint Propulsion Conference and Exhibit.

[30]XiongB, FanXQ, WangY, 2019. Parameterization and optimization design of a hypersonic inward turning inlet. Acta Astronautica, 164:130-141.

[31]XuSC, 2018. Design and Analysis of Hypersonic Inlet with Integrated Bump/Forebody. MS Thesis, National University of Defense Technology, Changsha, China(in Chinese).

[32]XuSC, WangY, WangZG, et al., 2017. The design and analysis of bump in high speed supersonic flow. Proceedings of the 21st AIAA International Space Planes and Hypersonics Technologies Conference.

[33]XuSC, WangY, WangZG, et al., 2019. Design and analysis of a hypersonic inlet with an integrated bump/forebody. Chinese Journal of Aeronautics, 32(10):2267-2274.

[34]YangYK, 2007. The research of bump inlet design and test. Acta Aerodynamica Sinica, 25(3):336-338 (in Chinese).

[35]YuZH, HuangGP, XiaC, 2018. Inverse design and Mach 6 experimental investigation of a pressure controllable bump. Aerospace Science and Technology, 81:204-212.

[36]YuZH, HuangGP, XiaC, et al., 2019. A pressure-controllable bump based on the pressure-ridge concept. Aerospace Science and Technology, 87:133-140.

[37]YuZH, HuangGP, XiaC, 2020. 3D inverse method of characteristics for hypersonic bump-inlet integration. Acta Astronautica, 166:11-22.

[38]YuanHC, LiuFZ, WangX, et al., 2021. Design and analysis of a supersonic axisymmetric inlet based on controllable bleed slots. Aerospace Science and Technology, 118:107008.

[39]YueLJ, JiaYN, XuX, et al., 2018. Effect of cowl shock on restart characteristics of simple ramp type hypersonic inlets with thin boundary layers. Aerospace Science and Technology, 74:72-80.

[40]ZhangBH, ZhaoYX, LiuJ, 2020. Effects of bleed hole size on supersonic boundary layer bleed mass flow rate. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 21(8):652-662.

[41]ZhangY, TanHJ, TianFC, et al., 2014. Control of incident shock/boundary-layer interaction by a two-dimensional bump. AIAA Journal, 52(4):767-776.

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