背负式进气道典型气动特性及流动机理

doi:10.7527/S1000-6893.2025.32314

Abstract

Abstract:

Numerical simulations were conducted to investigate the flow characteristics and flow formation mechanism of a typical layout of dorsal binary curved compression inlet at different angles of attack. The results show that the flow coefficient of the inlet and the total pressure recovery coefficient of the throat decrease simultaneously with the increase of the angle of attack， and the flow coefficient decreases by 24.4% and the total pressure recovery coefficient decreases by 14.8% when the angle of attack increases from 0° to 10°. The boundary layer diverter can effectively improve the flow coefficient and total pressure recovery coefficient of the inlet channel， the flow coefficient increases by about 4%， and the total pressure recovery coefficient of the throat channel increases by about 0.02. The analysis of the study shows that， with the increase of the angle of attack of the flight， the masking effect of the forebody on the dorsal inlet induces the appearance of the forebody expansion wave， which causes the acceleration of the airflow in front of the inlet. The higher Mach number and uneven distribution in front of the inlet are the main reasons for the simultaneous decrease of the flow coefficient and the total pressure recovery coefficient. Accordingly， a theoretical model of the flow characteristics of the forebody/inlet for this type of dorsal layout is established， which reveals the linear correlation between the Mach number in front of the inlet and the angle of attack， which can be used to predict the flow characteristics of the inlet accordingly. By changing the relative position of the inlet along the flow direction in the forebody， the influence of the boundary layer on the inlet flow can be improved， and the flow coefficient and total pressure recovery coefficient can be enhanced， but the enhancement is limited due to the fact that the Mach number in front of the inlet is still high and unevenly distributed.

Key words: dorsal inlet, boundary layer diverter, flow coefficient, angle of attack characteristic, expansion waves, linear relationship

CLC Number:

V211.48

Shanchao YANG, Hongyin LONG, Huacheng YUAN. Typical aerodynamic characteristics and flow mechanisms of dorsal inlet[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(24): 632314.

Figures/Tables 28

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References 21

[1]	向先宏，钱战森. 吸气式高超声速飞行器机体/推进一体化设计技术研究进展及分类对比分析［J］. 推进技术， 2018， 39（10）： 2207-2218.
	XIANG X H， QIAN Z S. An overview and development analysis of air-breathing hypersonic airframe/propulsion integrative design technology［J］. Journal of Propulsion Technology， 2018， 39（10）： 2207-2218 （in Chinese）.
[2]	郑晓刚，胡占仓，蔡泽君，等. 考虑巡航攻角的三维内转进气道设计［J］. 航空学报， 2025， 46（8）： 168-182.
	ZHENG X G， HU Z C， CAI Z J， et al. Design of 3D inward-turning inlet considering cruising angle of attack［J］. Acta Aeronautica et Astronautica Sinica， 2025， 46（8）： 168-182 （in Chinese）.
[3]	陈立立，郭正，侯中喜，等. 高超声速飞行器气动布局研究综述［J］. 空天技术， 2022（3）： 42-61.
	CHEN L L， GUO Z， HOU Z X， et al. Overview on aerodynamic configuration study of hypersonic vehicles［J］. Aerospace Technology， 2022（3）： 42-61 （in Chinese）.
[4]	李雪平，杨茂. 进气道布局对导弹气动性能影响的数值研究［J］. 科学技术与工程， 2010， 10（35）： 8747-8751.
	LI X P， YANG M. Numerical study of inlet configuration effects on aerodynamic performance for air-breathing missiles［J］. Science Technology and Engineering， 2010， 10（35）： 8747-8751 （in Chinese）.
[5]	郭宇辰. SR-72高超声速无人侦察机三维重建及其气动特性分析［D］. 南京：南京航空航天大学， 2016.
	GUO Y C. Three-dimensions reconstruction and analysis of aerodynamic of SR-72 hypersonic unmanned reconnaissance aircraft［D］. Nanjing： Nanjing University of Aeronautics and Astronautics， 2016 （in Chinese）.
[6]	赵克云. 大攻角（大侧滑角）下超音速后置旁侧进气道试验研究［J］. 推进技术， 1992， 13（3）： 35-40.
	ZHAO K Y. An experimental investigation on aft bypass supersonic inlet performance at high angle of attack and yaw［J］. Journal of Propulsion Technology， 1992， 13（3）： 35-40 （in Chinese）.
[7]	吕骞. 典型布局高超声速飞行器性能及内转式进气道起动性能研究［D］. 长沙：中南大学， 2023.
	LYU Q. Research on the performance of typical configuration hypersonic vehicle and the starting performance of inward turning inlet［D］. Changsha： Central South University， 2023 （in Chinese）.
[8]	STEELANT J， VILLACE V， KALLENBACH A， et al. Flight testing designs in HEXAFLY-INT for high-speed transportation［C］∥ 1st International Conference on High-speed Vehicle Science and Technology. Moscow： CESA， 2018： 3101064.
[9]	王海峰. 高性能战斗机与发动机协同设计关键技术［J］. 航空学报， 2024， 45（5）： 529978.
	WANG H F. Key technologies in collaborative airframe-engine design for high performance fighters［J］. Acta Aeronautica et Astronautica Sinica， 2024， 45（5）： 529978 （in Chinese）.
[10]	郁新华，刘斌，陶于金，等. 背负式进气道设计及其气动性能研究［J］. 西北工业大学学报， 2007， 25（2）： 270-273.
	YU X H， LIU B， TAO Y J， et al. Top-mounted inlet design and its aerodynamic performance［J］. Journal of Northwestern Polytechnical University， 2007， 25（2）： 270-273 （in Chinese）.
[11]	谭慧俊，郭荣伟. 一种背负式无附面层隔道进气道的数值模拟研究与实验验证［J］. 航空学报， 2004， 25（6）： 540-545.
	TAN H J， GUO R W. Numerical simulation investigation and experimental validation of a top-mounted diverterless inlet and its validation［J］. Acta Aeronautica et Astronautica Sinica， 2004， 25（6）： 540-545 （in Chinese）.
[12]	MURRAY N， STEELANT J. Methodologies involved in the design of LAPCAT-MR1： a hypersonic cruise passenger vehicle［C］∥ 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference. Reston： AIAA， 2009.
[13]	石磊，郭荣伟. 蛇形进气道的电磁散射特性［J］. 航空学报， 2007， 28（6）： 1296-1301.
	SHI L， GUO R W. Electromagnetic scattering characteristics of serpentine inlet［J］. Acta Aeronautica et Astronautica Sinica， 2007， 28（6）： 1296-1301 （in Chinese）.
[14]	刘甫州，袁化成，李东，等. 基于膨胀波效应的高超声速进气道肩部流动分离控制研究［J］. 推进技术， 2024， 45（1）： 68-80.
	LIU F Z， YUAN H C， LI D， et al. Investigation of flow separation controlling in hypersonic inlet shoulder based on expansion wave effect［J］. Journal of Propulsion Technology， 2024， 45（1）： 68-80 （in Chinese）.
[15]	阳未. 与飞行器前体一体化的可调进气道研究［D］. 南京：南京航空航天大学， 2020.
	YANG W. Research on variable geometry inlet integrated with the forebody of aircraft［D］. Nanjing： Nanjing University of Aeronautics and Astronautics， 2020 （in Chinese）.
[16]	黄河峡. 背景激波系干扰下隔离段内激波串特性及其控制研究［D］. 南京：南京航空航天大学， 2018.
	HUANG H X. Behaviors of shock train in isolator with background shocks and its control［D］. Nanjing： Nanjing University of Aeronautics and Astronautics， 2018 （in Chinese）.
[17]	TOWNSEND J C， VOLLMAR W R， VAS I E. The leading edge effect on the flow over a flat plate at M=10［R］. US： United States Air Force， 1966.
[18]	郭帅旗，刘文，张陈安，等. 高超声速钝前缘乘波构型优化设计研究［J］. 力学学报， 2022， 54（5）： 1414-1428.
	GUO S Q， LIU W， ZHANG C A， et al. Design and optimization for hypersonic cone-derived waverider with blunted leading-edge［J］. Chinese Journal of Theoretical and Applied Mechanics， 2022， 54（5）： 1414-1428 （in Chinese）.
[19]	BERENS T M， BISSINGER N C. Forebody precompression effects and inlet entry conditions for hypersonic vehicles［J］. Journal of Spacecraft and Rockets， 1998， 35（1）： 30-36.
[20]	吕宇超，胡姝瑶，蒋崇文，基于马赫线切割的楔形乘波前体改进设计研究［J］. 推进技术， 2018， 39（8）： 1696-1702.
	LYU Y C， HU S Y， JIANG C W. Improved design of wedge-derived waverider forebode based on Mach line cutting of compression surfaces［J］. Journal of Propulsion Technology， 2018， 39（8）： 1696-1702 （in Chinese）.
[21]	贾洪印，周桂宇，唐静，等. 带鼓包的背负式大S弯进气道流场特性及参数影响规律［J］. 西北工业大学学报， 2019， 37（3）： 572-579.
	JIA H Y， ZHOU G Y， TANG J， et al. Numerical investigation of dorsal S-shaped inlet flow characteristic and effects of related parameters［J］. Journal of Northwestern Polytechnical University， 2019， 37（3）： 572-579 （in Chinese）.

Typical aerodynamic characteristics and flow mechanisms of dorsal inlet

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