IMECH-IR  > 高温气体动力学国家重点实验室
Modification of hypersonic waveriders by vorticity-based boundary layer displacement thickness determination method
Liu W(刘文); Zhang CA(张陈安); Wang FM(王发民)
2018-04
发表期刊Aerospace Science and Technology
卷号75页码:200-214
摘要

For general hypersonic vehicles flying at high altitudes and Mach numbers, the appearance of the large boundary layer displacement thickness can change the pressure distribution and aerodynamic characteristics significantly. As for the waverider, another side effect is that the shock wave position is deflected downward evidently even at the design Mach number, which is adverse for the shock wave being attached to the leading edge and may lead to more leakage of high pressure gas from the lower surface onto the upper surface. Therefore, this paper first develops a vorticity-based method to determine the boundary layer displacement thickness, in combination with the tangent wedge/cone method. Then, trying to alleviate the high pressure gas leakage near the leading edge, modification of a viscous optimized waverider is conducted under the condition of strong viscous interaction, by deducting the corresponding boundary layer displacement thickness from the original lower surface along the normal direction. Results show that the shock wave position around the lower surface of the modified waverider under the condition of strong viscous interaction is very close to that of the inviscid basic flowfield around the original waverider, which means less leakage of high pressure gas. But it's found that such change has little influence on the aerodynamic characteristics of the upper surface. However, an interesting discovery is that due to the lower pressure near the leading edge of the modified lower surface, the wave drag is lowered for the same lift, thus the lift-to-drag ratio is improved. The modified waverider also exhibits higher lift-to-drag ratio at large angles of attack when compared to waveriders with upper expansion surfaces. Overall, a vorticity-based boundary layer displacement thickness determination method is proposed in this paper, which is then used to modify waveriders to achieve higher aerodynamic efficiency.

DOI10.1016/j.ast.2017.12.020
收录类别SCI ; EI
语种英语
力学所作者排名2
引用统计
文献类型期刊论文
条目标识符http://dspace.imech.ac.cn/handle/311007/77373
专题高温气体动力学国家重点实验室
通讯作者Zhang CA(张陈安)
作者单位1.Northwestern Polytechnical University, Xi'an 710072, People's Republic of China
2.Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, People's Republic of China
推荐引用方式
GB/T 7714
Liu W,Zhang CA,Wang FM. Modification of hypersonic waveriders by vorticity-based boundary layer displacement thickness determination method[J]. Aerospace Science and Technology,2018,75:200-214.
APA Liu W,Zhang CA,&Wang FM.(2018).Modification of hypersonic waveriders by vorticity-based boundary layer displacement thickness determination method.Aerospace Science and Technology,75,200-214.
MLA Liu W,et al."Modification of hypersonic waveriders by vorticity-based boundary layer displacement thickness determination method".Aerospace Science and Technology 75(2018):200-214.
条目包含的文件 下载所有文件
文件名称/大小 文献类型 版本类型 开放类型 使用许可
1-s2.0-S127096381731(2721KB)期刊论文出版稿开放获取CC BY-NC-SA浏览 下载
个性服务
推荐该条目
保存到收藏夹
查看访问统计
导出为Endnote文件
谷歌学术
谷歌学术中相似的文章
[Liu W(刘文)]的文章
[Zhang CA(张陈安)]的文章
[Wang FM(王发民)]的文章
百度学术
百度学术中相似的文章
[Liu W(刘文)]的文章
[Zhang CA(张陈安)]的文章
[Wang FM(王发民)]的文章
必应学术
必应学术中相似的文章
[Liu W(刘文)]的文章
[Zhang CA(张陈安)]的文章
[Wang FM(王发民)]的文章
相关权益政策
暂无数据
收藏/分享
文件名: 1-s2.0-S127096381731773X-main.pdf
格式: Adobe PDF
所有评论 (0)
暂无评论
 

除非特别说明,本系统中所有内容都受版权保护,并保留所有权利。