高速火箭增强冲压发动机内转进气道气动设计与风洞试验

doi:10.7527/S1000-6893.2025.32202

Abstract

Abstract:

Applying inward-turning inlet with high compression efficiency， good internal flow quality， high flow coefficient， and low overflow resistance to a rocket-augmented ramjet engine can effectively improve the performance of rocket-combined ramjet inlet within the typical flight range and greatly enhance the application potential of rocket-augmented ramjet engine. Based on the typical central strut configuration of a rocket-augmented ramjet engine， if only a simple structural integration method is adopted， the physical intervention of the central strut would seriously damage the compression performance of the inward-turning inlet while its wedge-shaped leading edge would divide the high-speed airflow downstream of the inlet isolator and cause oblique shock and expansion wave interference， resulting in additional compression and an increase in internal contraction ratio， causing a significant decrease in the total pressure recovery coefficient. To address these issues， this paper proposes a structural integration design method between an inward-turning inlet and central strut based on streamline tracing technique. By integrating the central strut with the inlet compression surfaces， not only additional compression effects can be eliminated， but the inflow compression capability of its special precursor can also be fully utilized. The numerical simulation and wind tunnel test verification results indicate that this design method can enable the integrated inward-turning inlet to fully exert the compression performance of the basic flow field while introducing the central strut. Compared with the traditional wedge-shaped central strut， its length can be reduced by 60% at most， and the internal contraction ratio can be reduced by 25%， thus ensuring better start capability. Under the conditions of high contraction ratio and strong compression with the incoming flow of Mach number 6 and the throat pressure rise ratio of 34.8， the total pressure recovery coefficient is improved by 17%.

Key words: rocket-augmented ramjet, inward-turning inlet, streamline tracing technique, central strut, wind tunnel test

CLC Number:

V438

Yiyan YANG, Anxiang FU, Yuhui WANG, Zhaoyang TIAN, Lei SHI. Aerodynamic design and wind tunnel test on inward-turning inlet of high-speed rocket-augmented ramjet engine[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(3): 132202.

Figures/Tables 26

Fig.1

Fig.2

Table 1

Fig.3

Fig.4

Fig.5

Fig.6

Fig.7

Fig.8

Fig.9

Table 2

Table 3

Fig.10

Fig.11

Fig.12

Table 4

Table 5

Fig.13

Fig.14

Fig.15

Fig.16

Fig.17

Fig.18

Fig.19

Fig.20

Fig.21

References 37

[1]	ESCHER W， SCHNURSTEIN R. A retrospective on early cryogenic primary rocket subsystem designs as integrated into rocket-based combined-cycle （RBCC） engines［C］∥29th Joint Propulsion Conference and Exhibit. Reston： AIAA， 1993.
[2]	EHRLICH C F. Early studies of RBCC applications and lessons learned for today［C］∥36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston： AIAA， 2000.
[3]	MCCLINTON C R， ANDREWS E H， HUNT J L. Engine development for space access： Past， present and future［C］∥15th International Symposium on Air Breathing Engines， 2001.
[4]	BILLIG F. SCRAM-A supersonic combustion ramjet missile［C］∥29th Joint Propulsion Conference and Exhibit. Reston： AIAA， 1993.
[5]	SHI L， YANG Y Y， ZHAO G J， et al. Research and development on inlets for rocket based combined cycle engines［J］. Progress in Aerospace Sciences， 2020， 117： 100639.
[6]	郑晓刚，施崇广，张加乐，等. 高超声速三维内转进气道研究进展综述［J］. 航空学报， 2025， 46（8）： 631245.
	ZHENG X G， SHI C G， ZHANG J L， et al. Research progress review on hypersonic three-dimensional inward-turning inlet［J］. Acta Aeronautica et Astronautica Sinica， 2025， 46（8）： 631245 （in Chinese）.
[7]	BILLIG F S， KOTHARI A P. Streamline tracing： Technique for designing hypersonic vehicles［J］. Journal of Propulsion and Power， 2000， 16（3）： 465-471.
[8]	BULMAN M， SIEBENHAAR A. The rebirth of round hypersonic propulsion［C］∥42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston： AIAA， 2006.
[9]	ZUO F Y， MÖLDER S， CHEN G. Performance of wavecatcher intakes at angles of attack and sideslip［J］. Chinese Journal of Aeronautics， 2021， 34（7）： 244-256.
[10]	TAYLOR T， VANWIE D. Performance analysis of hypersonic shape-changing inlets derived from morphing streamline traced flowpaths［C］∥15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Reston： AIAA， 2008.
[11]	孙波，张堃元，金志光，等. 流线追踪Busemann进气道设计参数的选择［J］. 推进技术， 2007， 28（1）： 55-59.
	SUN B， ZHANG K Y， JIN Z G， et al. Selection of design parameters for streamtraced hypersonic Busemann inlets［J］. Journal of Propulsion Technology， 2007， 28（1）： 55-59 （in Chinese）.
[12]	孙波，张堃元，王成鹏，等. Busemann进气道无粘流场数值分析［J］. 推进技术， 2005， 26（3）： 242-247.
	SUN B， ZHANG K Y， WANG C P， et al. Inviscid CFD analysis of hypersonic Busemann inlet［J］. Journal of Propulsion Technology， 2005， 26（3）： 242-247 （in Chinese）.
[13]	南向军，张堃元，金志光，等. 压升规律可控的高超声速内收缩进气道设计［J］. 航空动力学报， 2011， 26（3）： 518-523.
	NAN X J， ZHANG K Y， JIN Z G， et al. Investigation on hypersonic inward turning inlets with controlled pressure gradient［J］. Journal of Aerospace Power， 2011， 26（3）： 518-523 （in Chinese）.
[14]	南向军，张堃元. 采用新型基准流场的高超声速内收缩进气道性能分析［J］. 宇航学报， 2012， 33（2）： 254-259.
	NAN X J， ZHANG K Y. Analysis of hypersonic inward turning inlet with innovative axisymmetric basic flowfield［J］. Journal of Astronautics， 2012， 33（2）： 254-259 （in Chinese）.
[15]	卫锋. 基于特征线理论的流线追踪内转向进气道设计方法研究［D］. 长沙：国防科技大学， 2012： 13-34.
	WEI F. Investigation on design methodology for inward turning inlet based on the rotational method of characteristics［D］. Changsha： National University of Defense Technology， 2012： 13-34 （in Chinese）.
[16]	尤延铖，梁德旺，黄国平. 一种新型内乘波式进气道初步研究［J］. 推进技术， 2006， 27（3）： 252-256.
	YOU Y C， LIANG D W， HUANG G P. Investigation of internal waverider-derived hypersonic inlet［J］. Journal of Propulsion Technology， 2006， 27（3）： 252-256 （in Chinese）.
[17]	石磊，何国强，秦飞，等. 某RBCC样机进气道的设计与数值模拟［J］. 航空动力学报， 2011， 26（8）： 1801-1807.
	SHI L， HE G Q， QIN F， et al. Design and numerical investigation of RBCC prototype inlet［J］. Journal of Aerospace Power， 2011， 26（8）： 1801-1807 （in Chinese）.
[18]	刘宏宝. 矩形通道内支板对超声速流动影响的研究［D］. 天津：河北工业大学， 2018： 36-38.
	LIU H B. Study on the influence of the strut in the rectangular channel on the supersonic flow［D］. Tianjin： Hebei University of Technology， 2018： 36-38 （in Chinese）.
[19]	高逸夫，龚春林，王健磊，等. 中心支板参数对RBCC发动机性能影响研究［J］. 推进技术， 2022， 43（10）： 64-77.
	GAO Y F， GONG C L， WANG J L， et al. Effects of central-strut parameters on performance of RBCC engine［J］. Journal of Propulsion Technology， 2022， 43（10）： 64-77 （in Chinese）.
[20]	张正泽，刘佩进，秦飞，等. 中心支板顶角对RBCC进气道影响数值研究［J］. 推进技术， 2018， 39（4）： 768-775.
	ZHANG Z Z， LIU P J， QIN F， et al. Numerical investigation for effects of strut angle on RBCC inlet［J］. Journal of Propulsion Technology， 2018， 39（4）： 768-775 （in Chinese）.
[21]	薛龙生. 高超飞行器前体进气道一体化气动设计与试验研究［D］. 南京：南京航空航天大学， 2018： 20-32.
	XUE L S. Integrated aerodynamic design and experimental study on forebody and inlet of a hypersonic vehicle［D］. Nanjing： Nanjing University of Aeronautics and Astronautics， 2018： 20-32 （in Chinese）.
[22]	贺旭照，倪鸿礼. 密切内锥乘波体设计方法和性能分析［J］. 力学学报， 2011， 43（5）： 803-808.
	HE X Z， NI H L. Osculating inward turning cone（OIC） wave rider-design methods and performace analysis［J］. Chinese Journal of Theoretical and Applied Mechanics， 2011， 43（5）： 803-808 （in Chinese）.
[23]	HE X Z， LE J L， ZHOU Z， et al. Osculating inward turning cone waverider/inlet （OICWI） design methods and experimental study［C］∥18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference. Reston： AIAA， 2012.
[24]	贺旭照，秦思，周正，等. 一种乘波前体进气道的一体化设计及性能分析［J］. 航空动力学报， 2013， 28（6）： 1270-1276.
	HE X Z， QIN S， ZHOU Z， et al. Integrated design and performance analysis of waverider forebody and inlet［J］. Journal of Aerospace Power， 2013， 28（6）： 1270-1276 （in Chinese）.
[25]	贺旭照，周正，倪鸿礼. 密切内锥乘波前体进气道一体化设计和性能分析［J］. 推进技术， 2012， 33（4）： 510-515.
	HE X Z， ZHOU Z， NI H L. Integrated design methods and performance analyses of osculating inward turning cone waverider forebody inlet（OICWI）［J］. Journal of Propulsion Technology， 2012， 33（4）： 510-515 （in Chinese）.
[26]	李铮，袁化成，杨德壮. 基于三维内转式进气道的前体一体化设计［J］. 机械制造与自动化， 2023， 52（4）： 60-63.
	LI Z， YUAN H C， YANG D Z. Integrated design of osculating cone waverider forebody based on three-dimensional inward-turning inlet［J］. Machine Building & Automation， 2023， 52（4）： 60-63 （in Chinese）.
[27]	南向军，张堃元，金志光. 乘波前体两侧高超声速内收缩进气道一体化设计［J］. 航空学报， 2012， 33（8）： 1417-1426.
	NAN X J， ZHANG K Y， JIN Z G. Integrated design of waverider forebody and lateral hypersonic inward turning inlets［J］. Acta Aeronautica et Astronautica Sinica， 2012， 33（8）： 1417-1426 （in Chinese）.
[28]	WALKER S， RODGERS F. Falcon hypersonic technology overview［C］∥AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference. Reston： AIAA， 2005.
[29]	ELVIN J D. Integrated inward turning inlets and nozzles for hypersonic air vehicles： EP1818257A3［P］. 2009-12-16.
[30]	严岭峰. RBCC飞行器前体/进气道一体化气动构型设计［D］. 南京：南京航空航天大学， 2014： 21-55.
	YAN L F. Forebody/inlet integrative design of transatmospheric vehicle based on RBCC［D］. Nanjing： Nanjing University of Aeronautics and Astronautics， 2014： 21-55 （in Chinese）.
[31]	SHI L， YANG Y Y， YANG X， et al. Start limits and positive control of RBCC inlet［J］. Journal of Aerospace Engineering， 2022， 35（2）： 04021128.
[32]	马凯. 内嵌火箭冲压发动机燃烧室亚-超剪切层混合特性研究［D］. 西安：西北工业大学， 2020： 87-100.
	MA K. Investigation on the mixing features of subsonic-supersonic shear layer in ramjet with embedded rocket［D］. Xi’an： Northwestern Polytechnical University， 2020： 87-100 （in Chinese）.
[33]	HIRSCHEL E H. Basics of aerothermodynamics［M］. Berlin， Heidelberg： Springer， 2005： 230-232.
[34]	HU Z C， LI Z L， TANG Y Q， et al. Conceptual design methodology and performance evaluation of turbine-based combined cycle inward-turning inlet with twin-design points［J］. Aerospace Science and Technology， 2024， 152： 109309.
[35]	YANG Y Y， TIAN Z Y， YANG X， et al. Start/unstart hysteresis characteristics driven by embedded rocket of a rocket-based combined-cycle inlet［J］. Physics of Fluids， 2024， 36（8）： 086101.
[36]	SHI L， YANG Y Y， YANG X， et al. Experimental and numerical study on reinforcement mechanism of embedded rocket on back pressure resistance of RBCC inlet at starting stage［J］. Aerospace Science and Technology， 2022， 123： 107487.
[37]	武乐乐，何国强，秦飞，等. 中心支板钝化对RBCC进气道性能的影响［J］. 固体火箭技术， 2016， 39（5）： 606-611.
	WU L L， HE G Q， QIN F， et al. Influence of blunted central strut on performance of RBCC inlet［J］. Journal of Solid Rocket Technology， 2016， 39（5）： 606-611 （in Chinese）.

基准流场序号	a	b	c	唇口角度/（°）	总收缩比	内收缩比	喉部马赫数	喉部压升比	总压恢复系数
1	2.0	1.5	0.5	0	4.76	1.52	3.87	11.6	0.88
2	2.3	1.8	0.8	0	6.32	1.61	3.47	19.3	0.85
3	2.2	2.0	1.2	-2	8.16	1.71	3.14	28.5	0.78

进气道序号	总收缩比	内收缩比	喉部面积/mm²	出口面积/mm²	吸除面积/喉部面积	起动马赫数	自起动马赫数
1	4.6	1.50	2 236	52×45.5	0.38	2.7	3.1
2	6.2	1.60	1 619	44×38.5	0.36	3.2	3.5
3	7.6	1.66	1 324	40×35	0.30	3.6	3.8

来流马赫数	进气道序号	质量流量系数/%	总压恢复系数/%	吸除比/%	喉部马赫数	喉部升压比
4	1	76.5	81.3	2.6	2.3	9.3
	2	71.6	81.0	3.4	2.0	15.3
	3	69.2	77.5	4.9	1.7	23.1
6	1	97.2	72.8	0.8	3.5	13.5
	2	96.4	68.1	0.8	3.1	22.9
	3	96.4	61.7	0.8	2.7	34.8

进气道方案	喉部压升比	喉部马赫数	总压恢复系数/%
传统方案1	33.0	0.92	37.9
传统方案2	21.5	1.61	68.6
一体化方案	23.1	1.68	78.4

Aerodynamic design and wind tunnel test on inward-turning inlet of high-speed rocket-augmented ramjet engine

RichHTML

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

Figures/Tables 26

References 37

Related Articles 15

Recommended Articles

Metrics

Comments

[1]	Wei SUN, Yuni ZHANG, Ting LIU, Zheyu SHI, Yongfeng LIN. Experiment on influence mechanism of rotor flow on blade-vortex interaction noise [J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(3): 132182-132182.
[2]	Yang LIU, Yongjie SHI, Guohua XU. Wind tunnel test of rotor aerodynamic interference characteristics in complex low-altitude wind fields [J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(1): 632054-632054.
[3]	Kelei WANG, Zhou ZHOU, Minghao LI. Research and experimental validation of loose coupling design method for propulsion wing unit [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(9): 212-229.
[4]	Lixiang WEI, Jinglei XU, Kuangshi CHEN, Shuai HUANG, Jianhui GE, Guangtao SONG. Scheme design and performance study of adjustable vector nozzle for wide-range hypersonic aircraft [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(8): 631086-631086.
[5]	Xiaogang ZHENG, Zhancang HU, Zejun CAI, Chongguang SHI, Chengxiang ZHU, Yancheng YOU. Design of 3D inward-turning inlet considering cruising angle of attack [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(8): 631233-631233.
[6]	Xiaogang ZHENG, Chongguang SHI, Jiale ZHANG, Mi ZHANG, Wenlei ZHU, Chengxiang ZHU, Yancheng YOU. Research progress review on hypersonic three-dimensional inward-turning inlet [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(8): 631245-631245.
[7]	Xian YI, Jinghao REN, Qingren LAI, Yu LIU, Qiang WANG. Icing characteristics of full-scale multi-element configurations of large aircraft: Computation and experiment [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(5): 531575-531575.
[8]	Zhiqiang WAN, Shanshan ZHANG, Xiaozhe WANG, Liang MA, Ao XU, Zhigang WU, Chao YANG. Maneuver load analysis and alleviation technology of flexible aircraft: Review [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(3): 30279-030279.
[9]	Jun CHEN, Feng QU, Junjie FU. Design method of hypersonic inward turning inlet based on genetic and gradient hybrid optimization strategy [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(3): 130808-130808.
[10]	Bin LIANG, Junbo ZHAO, Zengliang FU, Jiajian ZHOU, Ping ZHOU, Shiyu ZHANG, Weiqi SUN. Effect of gas mass injection on pitching characteristics of blunt cone [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(3): 130822-130822.
[11]	Yong LIANG, Weiguo ZHANG, Binghui CHE, Honggang YUAN, Chunhua WEI, Ningmeng YANG. Wind tunnel tests of aeroacoustic characteristic for helicopter aircraft model [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(24): 132072-132072.
[12]	Junqiang WU, Zhi WEI, Yang LIU, Min ZHONG, Fujun YANG, Yonggang YU. Civil aircraft standard model system and construction of aerodynamic subject database [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(24): 132030-132030.
[13]	Wei WANG, Junfu LI, Fengxue QIAN, Yuting TAN, Yan ZHAO, Bowen ZHAO, Qing CHEN, Ke SONG. Wind tunnel test of low sonic boom high efficiency layout for supersonic civil aircraft [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(20): 531941-531941.
[14]	Hui ZHANG, Junqiang AI, Kun QIN, Xiangxi TANG, Jun JI. Wind tunnel test for thrust characteristics of supersonic ejector exhaust system [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(20): 531934-531934.
[15]	Zhengwu CHEN, Yubiao JIANG, Xiangyu LU, Qiangbin LI. Aerodynamic noise test of open rotor in wind tunnel [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(2): 130425-130425.