高超声速侧压式进气道溢流特性研究
Building and analysis of ontology based knowledge organizationmodel for aircraft engine design
-
摘要: 首先介绍了高超声速侧压式进气道的构型, 定义了侧压式进气道可能存在的两种溢流模态———构型溢流和压差溢流;然后对构型溢流进行了理论分析和计算, 阐明了侧板后掠的侧压进气道设计参数对构型溢流影响;最后对不同侧板配置方式的侧压式进气道进行了数值模拟, 通过对比分析发现由唇口板位置所决定的溢流窗大小对进气道溢流特性的影响显著.Abstract: Firstly configurations of the generic sidewall compression scramjet inlets were introduced and then two kinds of spillage that sidewall compression inlets might occur were introduced.Spillage induced by the back-swept sidewall leading edge is called Configuration Spillage,while spillage evoked by the pressure difference is described as Pressure-Driven Spillage.Parametric analysis of the inviscid effects of leading edge sweep,sidewall compression,width-height ratio,cowl position and inflow Mach number on spillage was carried out.Finally,numerical simulations were performed for a series of inlets at various flight altitude and speed.The research indicates that the area of spillage window,which is mainly determined by the position of the cowl,significantly influences the spillage characteristics of the scramjet inlet.
-
[1] Curran E T,Murthy S N B.Scramjet propulsion[M].American Institute of Aeronautics and Astronautics,Inc.2001. [2] Kumar A,Drummond J P,McClinton C R,Hunt J L.Research in hypersonic air-breathing propulsion at the NASA langley research center[R].ISABE-2001. [3] Holland S D.and Perkins J N.A computational parametric study of three-dimensional sidewall compression scramjet inlets at mach 10[R].AIAA-90-2131. [4] Holland S D.Mach 10 experimental database of a three-dimensional scramjet inlet flow field[R].NASA TM-4648,1995. [5] Holland S D.Internal shock interactions in propulsion/airframe integrated three-dimensional sidewall compression scramjet inlets[R],AIAA-92-3099. [6] 张堃元,萧旭东,徐辉.非均匀流等溢流角设计高超侧压进气道[J].推进技术,1998,19(1):20-24.ZHANG Kunyuan,XIAO Xudong,XU Hui.Hypersonic sidewall compression inlet with constant spillage angle design at non-uniforming flow[J].Journal of Propulsion Technology,1998,19(1):20-24. [7] 张堃元,王成鹏,杨建军,等.带高超进气道的隔离段流动特性[J].推进技术,2002,23 (4):311-314.ZHANG Kunyuan,WANG Chengpeng,YANG Jianjun,et al.Investigation of flow in isolator of hypersonic inlet[J].Journal of Propulsion Technology,2002,23 (4):311-314. [8] Cozart A B,Holland S D,Trexler C A.Leading edge sweep effects in generic three-dimensional sidewall compression scramjet inlets[R],AIAA 92-0674. [9] 李晓宇.高超声速飞行器乘波构型初步设计与分析[D],.长沙:国防科技大学,2002. [10] 贾地,范晓樯,李桦.侧板前缘后掠对侧压进气道性能影响的研究[A].全国高超声速气动力(热)交流会学术论文集[C](第十三届) 黄山:2005. [11] Ye Fangrong,Huque Z,Butuk N.Effect of sidewall leading edge sweep direction on performance of a hyper-sonic 3-D inlet[R],AIAA-2000-3600. [12] 范晓樯,李桦,丁猛.等截面矩形隔离段内流场的三维数值模拟[J].推进技术,2002,23 (2):129-131.FAN Xiaoqiang,LI Hua,DING Meng.3-D numerical simulation on inner flow field in rectangular cross section isolator[J].Journal of Propulsion Technology,2002,23 (2):129-131. [13] 徐惊雷,张堃元.唇口对侧压式高超声速进气道及等直隔离段影响的数值分析[J].航空动力学报,2004,19(6):806-810.XU Jinglei,ZHANG Kunyuan.The numerical study of the cowl effect on the sidewall compression hypersonic inlet and isolator[J].Journal of Aerospace Power,2004,19(6):806-810.
点击查看大图
计量
- 文章访问数: 1534
- HTML浏览量: 1
- PDF量: 427
- 被引次数: 0