高超声速内转式进气道型面流场重构

doi:10.7527/S1000-6893.2019.23493

流体力学与飞行力学

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高超声速内转式进气道型面流场重构

王卫星¹, 朱婷², 张仁涛¹, 李宥晨¹

1. 南京航空航天大学能源与动力学院, 南京 210016;
2. 中国商飞上海飞机设计研究院, 上海 200120

收稿日期:2019-09-12 修回日期:2019-12-16 出版日期:2020-03-15 发布日期:2019-12-12
通讯作者: 王卫星 E-mail:wangweixing@nuaa.edu.cn
基金资助:
国家自然科学基金（11502111）；航空科学基金（2014ZB52022）

Flow field reconstruction of hypersonic inward turning inlet based on configuration

WANG Weixing¹, ZHU Ting², ZHANG Rentao¹, LI Youchen¹

1. College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. COMAC Shanghai Aircraft Design and Research Institute, Shanghai 200120, China

Received:2019-09-12 Revised:2019-12-16 Online:2020-03-15 Published:2019-12-12
Supported by:
National Natural Science Foundation of China (11502111); Aeronautical Science Foundation of China(2014ZB52022)

摘要/Abstract

摘要： 内转式进气道流场参数分布不均，为改善该类进气道的气动性能，本文采用数值仿真方法开展了基于型面的内转式进气道流场重构研究。结果表明：流场重构型面中心线对进气道流场结构及流动特性影响较大，在给定偏距/长度与中心线末端斜率的约束条件下，选取合适的中心线起始角能够大幅提高进气道的气动性能，改善流场参数分布。与进气道原型方案相比，流场重构型面中心线10°起始角的进气道方案总压恢复系数、抗反压能力最大分别提升33.7%、26.4%，自起动马赫数下降1.1。随着流场重构型面中心线起始角增大，唇罩激波/侧壁边界层干扰诱发的流向涡减弱、流向涡传输轨迹向唇罩一侧偏移，低能流向唇罩两侧迁移趋势增强。在研究范围内，随着流场重构型面中心线起始角增大，隔离段出口总压恢复系数先增大后减小，自起动马赫数先下降后不变。

关键词: 内转式进气道, 流动特性, 激波/边界层干扰, 流向涡, 气动性能

Abstract: The distribution of flow field parameters of inward turning inlet is uneven. In order to improve the aerodynamic performances of inward turning inlet, a numerical simulation method is employed to study the flow field reconstruction of inward inlet based on the configuration. The results show that the centerline of the flow field reconstruction surface largely influences the flow field structure and flow characteristics of inlet. Under the given offset distance/length and slope at the end of centerline, the aerodynamic performances and the distribution of flow field parameters of the inlet at appropriate initial angle of centerline are improved. Compared with the basic inward turning inlet, at centerline initial angle 10°, the total pressure recovery at outlet and the back pressure capability of the inlet improved by 33.7% and 26.4%, and the self-starting Mach number decreased by 1.1. As the initial angle of the centerline increases, the streamwise vortex induced by the shock/sidewall boundary layer interaction weakens and the trajectory of streamwise vortex shifts to the cowl side from ramp, and the migration of flow with low total pressure to cowl on both sides enhances. Within the research scope, as the initial angle of centerline increases, the total pressure recovery of the outlet increases firstly and then decreases, and the self-starting Mach number decreases firstly and then remains constant.

Key words: inward turning inlet, flow characteristics, shock/boundary layer interaction, stream wise vortex, aerodynamic performance

中图分类号:

V211.3

王卫星, 朱婷, 张仁涛, 李宥晨. 高超声速内转式进气道型面流场重构[J]. 航空学报, 2020, 41(3): 123493-123493.

WANG Weixing, ZHU Ting, ZHANG Rentao, LI Youchen. Flow field reconstruction of hypersonic inward turning inlet based on configuration[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(3): 123493-123493.

参考文献 28

[1]	BILLIG F S, JACOBSEN L S. Comparison of planar and axisymmetric flowpaths for hydrogen fueled space access vehicles:AIAA-2003-4407[R]. Reston, VA:AIAA, 2003.
[2]	ZANCHETTA M, CAIN T. An axisymmetric internal compression inlet:AIAA-1998-1525[R]. Reston, VA:AIAA, 1998.
[3]	GOLDFELD M, NESTOULIA R. Numerical and experimental studies of 3D hypersonic inlet[J]. Jornal of Thermal Science, 2002, 11(3):198-206.
[4]	BARKMEYER D, STARKEY R, LEWIS M. Inverse waverider design for inward turning inlets[C]//41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, VA:AIAA, 2005.
[5]	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.
[6]	SMART M K, WHITE J A. Computational investigation of the performance and back-pressure limits of a hypersonic inlet[C]//AIAA Aerospace Sciences Meeting & Exhibit. Reston, VA:AIAA, 2002.
[7]	SMART M K. Experimental testing of a hypersonic inlet with rectangular-to-elliptical shape transition[J]. Journal of Propulsion and Power, 2001, 17(2):276-283.
[8]	SMART M K. Design of three-dimensional hypersonic inlets with rectangular-to-elliptical shape transition[J]. Journal of Propulsion and Power, 1999, 15(3):408-416.
[9]	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 and performance analysis of inner cone wave-riding precursor inlet[J]. Journal of Propulsion Technology, 2012, 33(4):510-515 (in Chinese).
[10]	YOU Y C, LIANG D W, HUANG G P. Cross section controllable hypersonic inlet design using streamline-tracing and osculating axisymmetric concepts[C]//43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, VA:AIAA, 2007.
[11]	YOU Y C,LIANG D W.Design concept of three-dimensional section controllable internal waverider hypersonic inlet[J]. Science in China, 2009, 52(7):2017-2028.
[12]	YOU Y C, LIANG D W, GUO R W. High enthalpy wind tunnel tests of three-dimensional section controllable internal waverider hypersonic inlet[C]//47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition. Reston, VA:AIAA, 2009.
[13]	尤延铖, 梁德旺. 基于内乘波概念的三维变截面高超声速进气道[J]. 中国科学:技术科学,2009(8):1483-1494. YOU Y C,LIANG D W.Hypersonic inlet with three dimensional variable cross-section based on internal riding wave concept[J]. Science China:Technological Science,2009(8):1483-1494 (in Chinese).
[14]	XIAO Y B, YUE L J, CHEN L C, et al. Iso-contraction-ratio methodology for the design of hypersonic inward turning inlets with shape transition[C]//18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference. Reston, VA:AIAA, 2012.
[15]	MATTHEWS A J, JONES T V. Design and test of a modular waverider hypersonic intake[J]. Journal of Propulsion and Power, 2006, 22(4):913-920.
[16]	NAN X J, ZHANG K Y. Numerical and experimental investigation on hypersonic inward turning inlets with basic flowfield using arc tangent curve law of pressure rise[C]//AIAA International Space Planes & Hypersonic Systems & Technologies Conference. Reston, VA:AIAA, 2011.
[17]	李永洲,张堃元,南向军.基于马赫数分布规律可控概念的高超声速内收缩进气道设计[J]. 航空动力学报, 2012, 27(11):2484-2491. LI Y Z, ZHANG K Y, NAN X J. Hypersonic internal contraction inlet design based on the controllable concept of Mach number distribution law[J]. Journal of Aerospace Power, 2012, 27(11):2484-2491 (in Chinese).
[18]	QIAO W Y, YU A Y, GAO W, et al. Design method with controllable velocity direction at throat for inward-turning inlets[J]. Chinese Journal of Aeronautics, 2019, 32(6):1403-1415.
[19]	乔文友, 黄国平, 夏晨, 等. 发展用于高速飞行器前体/进气道匹配设计的逆特征线法[J]. 航空动力学报, 2014, 29(6):1444-1452. QIAO W Y, HUANG G P, XIA C, et al. Development of inverse characteristic method for precursor/inlet matching design of high speed aircraft[J].Journal of Aerospace Power, 2014, 29(6):1444-1452 (in Chinese).
[20]	王卫星, 郭荣伟. 圆形出口内转式进气道流动特征[J].航空学报, 2016, 37(2):533-544. WANG W X, GUO R W. Flow characteristics of inner rotary inlet at circular outlet[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(2):533-544 (in Chinese).
[21]	王卫星, 顾强, 郭荣伟. 内转式进气道流动控制研究[J]. 推进技术, 2017, 38(5):6-12. WANG W X, GU Q, GUO R W. A study on the flow control of inward-rotating inlet[J]. Journal of Propulsion Technology, 2017, 38(5):6-12 (in Chinese).
[22]	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. NAN X J, ZHANG K Y, JIN Z G. Hypersonic internal contraction inlet test using a new type of basic flow field[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(1):90-96 (in Chinese).
[23]	王德鹏, 田方超, 张启帆, 等. 进口形状对内转式进气道的起动特性影响[J]. 航空动力学报, 2015, 30(6):1400-1406. WANG D P, TIAN F C, ZHANG Q F, et al. Effect of inlet shape on starting characteristics of inward-turning inlet[J]. Journal of Aerospace Power, 2015, 30(6):1400-1406 (in Chinese).
[24]	田方超, 张启帆, 谭慧俊. 内收缩进气道不起动非定常流动研究[C]//高超声速冲压发动机内外流耦合流动研讨会, 2013. TIAN F C, ZHANG Q F, TAN H J. Study on unsteady flow of internal contraction inlet without starting[C]//Hypersonic Ram Internal and External Coupled Flow Seminar, 2013 (in Chinese).
[25]	JACOBSEN L S, TAM C J, BEHDADNIA R, et al. Starting and operation of a streamline-traced busemann inlet at Mach 4[C]//AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, VA:AIAA, 2006.
[26]	ANDREAS K F, ALI G.Experimental investigation of the starting behavior of a three-dimensional SCRamjet intake with a movable cowl and exchangeable cowl geometry at different Mach numbers[J]. 19th AIAA International Space Planes and Hypersonic and Systems and Technologies Conference. Reston, VA:AIAA, 2014.
[27]	朱婷, 王卫星. 唇罩内型面对内转式进气道流动特性影响研究[J]. 推进技术, 2019, 40(10):2226-2234. ZHU T, WANG W X. Study on the influence of inner lip mask on inward-turning inlet flow characteristics[J]. Journal of Propulsion Technology, 2019, 40(10):2226-2234 (in Chinese).
[28]	DOLLING D S MCCLURE W B. Flowfield scaling in sharp fin-induced shock wave/turbulent boundary-layer interaction[J]. AIAA Journal, 1985, 23(2):201-206.

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

高超声速内转式进气道型面流场重构

Flow field reconstruction of hypersonic inward turning inlet based on configuration

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