Shock Impingement Caused by Boundary-Layer Separation Ahead of Blunt Fins
Author:
Affiliation:
1. Grumman Aerospace Corporation, Bethpage, N.Y.
2. Aerospace Research Laboratories, Wright-Patterson Air Force Base, Ohio
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.50590
Reference4 articles.
1. Survey of viscous interactions associated with high Mach number flight
2. Fluctuating Pressures Induced by Three‐Dimensional Protuberances
3. Shock Interference Bell Aerospace, Heating in Hypersonic Flows
Cited by 19 articles. 订阅此论文施引文献 订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献
1. PSP Investigation of a Hemispherically Rounded Blunt Fin over a Compliant Panel in Supersonic Flow;AIAA SCITECH 2024 Forum;2024-01-04
2. Fluid-Structure Interactions of a Hemispherically Rounded Blunt Fin over a Compliant Panel in Mach 2 Flow;AIAA AVIATION 2023 Forum;2023-06-08
3. Experimental Characterization of Supersonic Flow over a Wall-Mounted Hemisphere;AIAA Journal;2021-11
4. Flow Structure and Heat Transfer Characterization of a Blunt-Fin-Induced Shock-Wave/Laminar Boundary-Layer Interaction;AIAA Scitech 2021 Forum;2021-01-04
5. Exploration of Upstream Influence and the Role of Shock Generator Geometry in Shock Wave/Transitional Boundary Layer Interactions at Mach 1.8 Edge Conditions;AIAA AVIATION 2020 FORUM;2020-06-08
1.学者识别学者识别
2.学术分析学术分析
3.人才评估人才评估
"同舟云学术"是以全球学者为主线，采集、加工和组织学术论文而形成的新型学术文献查询和分析系统，可以对全球学者进行文献检索和人才价值评估。用户可以通过关注某些学科领域的顶尖人物而持续追踪该领域的学科进展和研究前沿。经过近期的数据扩容，当前同舟云学术共收录了国内外主流学术期刊6万余种，收集的期刊论文及会议论文总量共计约1.5亿篇，并以每天添加12000余篇中外论文的速度递增。我们也可以为用户提供个性化、定制化的学者数据。欢迎来电咨询！咨询电话：010-8811{复制后删除}0370
www.globalauthorid.com
TOP
Copyright © 2019-2024 北京同舟云网络信息技术有限公司 京公网安备11010802033243号 京ICP备18003416号-3