一体化乘波进气道改进设计和流动特征分析

曲俐鹏; 曾学军; 余安远; 杨大伟

doi:10.13224/j.cnki.jasp.2018.04.012

一体化乘波进气道改进设计和流动特征分析

doi: 10.13224/j.cnki.jasp.2018.04.012

中国空气动力研究与发展中心超高速空气动力研究所高超声速冲压发动机技术重点实验室，四川绵阳 621000

基金项目: 国家自然科学基金（51376192）

计量
- 文章访问数: 951
- HTML浏览量: 3
- PDF量: 979
- 被引次数: 0
出版历程
- 收稿日期: 2016-10-30
- 刊出日期: 2018-04-28

Improving design and flow characteristics analysis ofan integrated wave-rider inlet

摘要

摘要: 为提高一体化乘波进气道的性能，通过采用壁面马赫数反正切分布内收缩基准流场和改进密切轴对称过程中的控制型线实现了对一体化乘波进气道的改进设计。通过数值仿真分析了该构型设计与非设计状态下的性能和流动特征。结果表明：设计状态下，该构型性能优良，具有前体/进气道一体化设计的特点，压缩面切除造成压缩面边界层内存在横向流动。不同攻角来流状态下，前缘弯曲激波的形状变化较小，有助于提高进气道非设计工况下的性能。侧滑来流状态下，内压缩段的流动不均匀，该构型的性能随侧滑角的变化是非线性的，内压缩段背风侧会出现低压区，诱导出流向涡，当截面内的气流流向低压区时，内压缩段内会形成双涡结构，当气流流出低压区时，第二个涡会被耗散掉，形成单涡结构。
- 一体化乘波进气道 /
- 内收缩基准流场 /
- 密切轴对称方法 /
- 流向涡 /
- 进气道设计
Abstract: For improving the performance of an integrated wave-rider inlet, the arc tangent Mach number basal flow and enhanced osculating axisymmetric control lines were adopted in the design process. Numerical simulation was conducted at on-design and off-design conditions and flow characteristics were analyzed respectively. At the design condition, the wave-rider inlet had excellent performance and the characteristic of forebody/inlet integration, however, the cross-flow phenomena appeared in the boundary-layer of compression surface as a result of cutting off. At different angles of attack, the configurations of leading edge shock were nearly the same, helping to enhance the flow capture capability at off-design conditions. For different angles of sideslip, the regularity of the performance varying with angle of sideslip was nonlinear as a result of flows ununiformity. A low-pressure region appeared at the leeward side of inner compression part, leading to a stream wise vortex. As the gas flowed to the low-pressure region on different slices, a dual-vortex structure was formed at the inner compression part. As the gas flowed out of low-pressure region, the second vortex was dissipated.
- integrated wave-rider inlet /
- inward-turning basal flow /
- osculating axisymmetric method /
- streamwise vortex /
- inlet design

HTML

参考文献(21)

[1]	蔡国彪,徐大军.高超声速飞行器技术［M］.北京:科学出版社，2012.
[2]	CURRAN E T,MURTHY S N B.Scramjet propulsion,progress in astronautics and aeronautics［M］.Virginia:American Institute of Aeronautics and Astronautics,2001.
[3]	吴先宇,刘睿,罗世彬,等.基于替代模型的高超声速前体/进气道一体化优化［J］.航空动力学报,2008,23(5):796-802.WU Xianyu,LIU Rui,LUO Shibin,et al.An integrated optimization of hypersonic forebody/inlet based on surrogate models［J］.Journal of Aerospace Power,2008,23(5):796-802.(in Chinese)
[4]	陈雪冬,王发民.钝化前缘乘波布局及其一体化构型气动特性［J］.航空动力学报,2013,28(2):379-384.CHEN Xuedong,WANG Famin.Aerodynamic characteristics of waverider and its integrated configuration with blunt leading edge［J］.Journal of Aerospace Power,2013,28(2):379-384.(in Chinese)
[5]	HUANG G P,ZHOU M,CHEN J,et al.A new combined design of inlet and forebody for high-speed vehicle［R］.AIAA-2011-5828,2011.
[6]	GOLLAN R J,SMART M K.Design of modular shape-transition inlets for a conical hypersonic vehicle［J］.Journal of Propulsion and Power,2013,29(4):832-838.
[7]	JAVAID K H,SERGHIDES V C.Airframe-propulsion integration methodology for waverider-derived hypersonic cruise aircraft design concepts［J］.Journal of Spacecraft and Rockets,2005,42(4):663-671.
[8]	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 Xuzhao,QIN Si,ZHOU Zheng,et al.Integrated design and performance analysis of waverider forebody and inlet［J］.Journal of Aerospace Power,2013,28(6):1270-1276.(in Chinese)
[9]	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)：896-902.HE Xuzhao,NI Hongli.Osculating inward turning cone design methods and performance analysis［J］.Chinese Journal of Theoretical and Applied Mechanics,2011,43(5):896-902.(in Chinese)
[10]	卫锋,贺旭照,贺元元,等.三维内转式进气道双激波基准流场的设计方法［J］.推进技术,2015,36(3):358-364.WEI Feng,HE Xuzhao,HE Yuanyuan,et al.Design method of dual-shock wave basic flow-field for inward turning inlet［J］.Journal of Propulsion Technology,2015,36(3):358-364.(in Chinese)
[11]	南向军.压升规律可控的高超声速内收缩进气道设计方法研究［D］.南京:南京航空航天大学,2012.NAN Xiangjun.Investigation on design methodology of hypersonic inward turning inlets with controlled pressure rise law［D］.Nanjing:Nanjing University of Aeronautics and Astronautics,2012.(in Chinese)
[12]	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 Yongzhou,ZHANG Kunyuan,NAN Xiangjun.Design of hypersonic inward turning inlets base on concept of controllable Mach number distribution［J］.Journal of Aerospace Power,2012,27(11):2484-2491.(in Chinese)
[13]	李永洲,张堃元,钟启涛.型面设计马赫数对马赫数分布可控高超声速内收缩进气道的影响［J］.南京航空航天大学学报,2014,46(2):239-245.LI Yongzhou,ZHANG Kunyuan,ZHONG Qitao,et al.Influence of design Mach number on hypersonic inward turning inlets with controllable Mach number distribution［J］.Journal of Nanjing University of Aeronautics and Astronautics,2014,46(2):239-245.(in Chinese)
[14]	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:E辑技术科学,2009,39(8):1483-1494.YOU Yancheng,LIANG Dewang.Design concept of the three-dimension section controllable internal waverider hypersonic inlet［J］.Science China:E Technological Sciences,2009,39(8):1483-1494.(in Chinese)
[15]	吴颖川,贺元元,贺伟,等.基于密切曲锥的乘波构型一体化飞行器设计方法研究［J］.空气动力学学报,2014,32(1):8-12.WU Yingchuan,HE Yuanyuan,HE Wei,et al.The design of osculating curved cone waverider based hypersonic vehicle［J］.Acta Aerodynamica Sinica,2014,32(1):8-12.(in Chinese)
[16]	吴颖川,贺元元,余安远,等.展向截断曲面乘波压缩进气道气动布局［J］.航空动力学报,2013,28(7):1570-1575.WU Yingchuan,HE Yuanyuan,YU Anyuan,et al.Aerodynamic layout of spanwise truncated curved waverider compression inlet［J］.Journal of Aerospace Power,2013,28(7):1570-1575.(in Chinese)
[17]	赵慧勇.超燃冲压整体发动机并行数值研究［D］.四川绵阳:中国空气动力研究与发展中心，2005.ZHAO Huiyong.Parallel numerical study of whole scramjet engine［D］.Mianyang Sichuan:China Aerodynamics Research and Development Center,2005.(in Chinese)
[18]	贺元元,乐嘉陵,倪鸿礼.吸气式高超声速机体/推进一体化飞行器数值和试验研究［J］.实验流体力学,2007,21(2):29-34.HE Yuanyuan,LE Jialing,NI Hongli.Numerical and experimental study of air-breathing hypersonic airframe/propulsion integrative vehicle［J］.Journal of Experiments in Fluid Mechanics,2007,21(2):29-34.(in Chinese)
[19]	HE Xuzhao,LE Jialing,ZHOU Zheng,et al.Osculating inward turning cone waverider/inlet (OICWI) design methods and experimental study［R］.AIAA-2012-5810,2012.
[20]	ALVI F S,SETTLES G S.Physical model of the swept shock wave/boundary-layer interaction flowfield［J］.AIAA Journal，1992,30(9):2252-2258.
[21]	梁德旺,李博.某典型二元高超声速进气道内二次流分析［J］.推进技术,2005,26(2):139-143.LIANG Dewang,LI Bo.Analysis of secondary vortex in a 2-D typical scramjet inlet［J］.Journal of Propulsion Technology,2005,26(2):139-143.(in Chinese)