帮助 关于我们

返回检索结果

高速进气道低马赫数不起动特性及马赫数影响规律
Unstart Characteristics of High Speed Inlet at Low Mach Number and Influence Law of Mach Number

查看参考文献24篇

贺理浩 1,2   张启帆 1 *   岳连捷 1   张新宇 1,2   王卫星 3   谭慧俊 3  
文摘 为了探究进气道低马赫数不起动时的振荡特性,本文结合一体化前体/进气道构型,通过非定常仿真手段,对比研究了来流马赫数变化对进气道低马赫数不起动振荡流场以及飞行器气动力的影响规律。结果表明:低马赫数不起动时出现了稳定的振荡周期,且周期随着来流马赫数的增大而增长。由于拥塞发生在喉道处,其振荡流场单纯地表现为口部分离包的涨大和缩小,并且沿程压力的均值和幅值都呈现出喉道高两头低的分布趋势,而马赫数的增大会加剧此趋势。喘振周期中升力系数C_L和阻力系数C_D的变化趋势大致相反,升阻比曲线则表现为随分离包吐出而增大、吞入而缩小的趋势。C_L和C_D随着马赫数增大是整体下降的,但是脉动幅值变化不大,升阻比对马赫数的变化也并不敏感。此外,在进气道实现自起动过程中,当喉道瞬时流量高于起动时的流量一定程度,口部分离包将完全吞入。但定常仿真难以准确模拟该吞入过程,因此定常仿真得到的自起动马赫数偏高。
其他语种文摘 In order to explore the oscillation characteristics of the inlet unstart induced by the low Mach number inflow,an unsteady simulation study of a specific integration of the forebody and the inlet was carried out. A comparison of the oscillation flow field and the aerodynamic force of the aircraft under different incoming Mach numbers were performed. The results show that a stable periodic oscillation appears when the inlet is unstart at the low Mach number. And the cycle length of the periodic oscillation increases with the increase of the incoming Mach number. Due to the throttling in the inlet throat,the oscillation flow field can be divided into two stages,which are the increasing and decreasing stages of the separation bubble in the throat. Meanwhile,the distribution trends of the mean and amplitude of the pressure along the tunnel both exhibit high at throat and low at both ends. And the increase of inflow Mach number will increase such trend. In the oscillation period,the variation trends of the lift coefficient C_L and the drag coefficient C_D are quite different,while the lift drag ratio curve is manifested as the trend of increasing with the throwing up of the separation bubble and decreasing with the swallowing of the separation bubble. C_L and C_D decrease with the increase of Mach number,but the amplitude of pulsation changes little,and the lift drag ratio is not sensitive to the change of Mach number. C_L and C_D both decrease with the increase of Mach number,but the amplitude of oscillation changes little. And the lift-drag ratio is not sensitive to the change of Mach number. In addition,in the process of self-starting,it is found that once the instantaneous flow in the throat is higher than that in the starting to a certain extent,the separation bubble at the throat can be swallowed completely. Because the swallowing process cannot be simulated by the steady simulation accurately,the self-starting Mach number obtained by the steady simulation is higher.
来源 推进技术 ,2021,42(10):2207-2217 【核心库】
DOI 10.13675/j.cnki.tjjs.200090
关键词 高速进气道 ; 低马赫数不起动 ; 非定常 ; 气动力 ; 自起动
地址

1. 中国科学院力学研究所, 高温气体动力学国家重点实验室, 北京, 100190  

2. 中国科学院大学工程科学学院, 北京, 100049  

3. 南京航空航天大学能源与动力学院, 江苏, 南京, 210016

语种 中文
文献类型 研究性论文
ISSN 1001-4055
学科 航空
基金 国家自然科学基金
文献收藏号 CSCD:7067276

参考文献 共 24 共2页

1.  蔡国飙. 高超声速飞行器技术,2012 被引 20 次    
2.  陈英硕. 国外吸气式高超声速飞行器发展现状. 飞航导弹,2008(12):25-32 被引 4 次    
3.  Curran E T. Scramjet Propulsion,2001 被引 8 次    
4.  Oswatitsch K. Pressure Recovery for Missiles with Reaction Propulsion at High Supersonic Speeds. NACA-TM-1140,1944 被引 1 次    
5.  Newsome R W. Numerical Simulation of Near-Critical and Unsteady,Subcritical Inlet Flow. AIAA Journal,1984,22(10):1375-1379 被引 12 次    
6.  Lu P J. Numerical Investigation of Inlet Buzz Flow. Journal of Propulsion and Power,1998,14(1):90-100 被引 13 次    
7.  Trapier S. Experimental Study of Supersonic Inlet Buzz. AIAA Journal,2006,44(10):2354-2365 被引 20 次    
8.  Trapier S. Time Frequency Analysis and Detection of Supersonic Inlet Buzz. AIAA Journal,2007,45(9):2273-2284 被引 8 次    
9.  Trapier S. Delayed Detached-Eddy Simulation and Analysis of Supersonic Inlet Buzz. AIAA Journal,2008,46(1):118-131 被引 9 次    
10.  Lee H J. Flow Characteristics of Small-Sized Supersonic Inlets. Journal of Propulsion and Power,2011,27(2):306-318 被引 12 次    
11.  Soltani M R. Effects of Angle of Attack on the Inlet Buzz. Journal of Propulsion and Power,2012,28(4):747-757 被引 4 次    
12.  Herrmann D. Pressure Fluctuations (Buzzing)and Inlet Performance of an Airbreathing Missile. Journal of Propulsion and Power,2013,29(4):839-848 被引 7 次    
13.  Mcclinton C R. Airbreathing Hypersonic Technology Vision Vehicles and Development Dreams. AIAA 99-4987 被引 2 次    
14.  Tan H J. Oscillatory Flows of Rectangular Hypersonic Inlet Unstart Caused by Downstream Mass-Flow Choking. Journal of Propulsion and Power,2009,25(1):138-147 被引 25 次    
15.  Tan H J. Experimental Investigation of the Unstart Process of a Generic Hypersonic Inlet. AIAA Journal,2011,49(2):279-288 被引 21 次    
16.  Wagner J L. Experimental Investigation of Unstart in an Inlet/Isolator Model in Mach 5 Flow. AIAA Journal,2009,47(6):1528-1542 被引 30 次    
17.  Wagner J L. Velocimetry Measurements of Unstart in an Inlet-Isolator Model in Mach 5 Flow. AIAA Journal,2010,48(9):1875-1888 被引 20 次    
18.  Li Z F. Unsteady Behaviors of a Hypersonic Inlet Caused by Throttling in Shock Tunnel. AIAA Journal,2013,51(10):2485-2492 被引 25 次    
19.  Chang J T. Novel Oscillatory Patterns of Hypersonic Inlet Buzz. Journal of Propulsion and Power,2012,28(6):1214-1221 被引 11 次    
20.  Zhang Q F. Unstart of a Hypersonic Inlet with Side Compression Caused by Downstream Choking. AIAA Journal,2016,1(54):28-38 被引 2 次    
引证文献 3 篇

1 叶柳青 振荡激波作用下壁板的非线性动力学特性分析 振动工程学报,2022,35(2):464-474
被引 0 次

2 叶柳青 振荡激波作用下受热壁板主共振特性分析 振动与冲击,2022,41(9):41-50
被引 0 次

显示所有3篇文献

论文科学数据集
PlumX Metrics
相关文献

 作者相关
 关键词相关
 参考文献相关

版权所有 ©2008 中国科学院文献情报中心 制作维护：中国科学院文献情报中心
地址：北京中关村北四环西路33号 邮政编码：100190 联系电话：(010)82627496 E-mail:cscd@mail.las.ac.cn 京ICP备05002861号-4 | 京公网安备11010802043238号