Visualization of Hypersonic Compression Corner Flows Using Temperature- and Pressure-Sensitive Paints
Author:
Affiliation:
1. Tohoku University
2. Japan Aerospace Exploration Agency (JAXA)
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2007-118
Reference20 articles.
1. Heat transfer from hypersonic turbulent flow at a wedge compression corner
2. The interaction of a shock wave with a laminar boundary layer at a compression corner in high-enthalpy flows including real gas effects
3. Separation length in high-enthalpy shock/boundary-layer interaction
4. Experimental study of flow unsteadiness in a Mach 9 compression ramp interaction using a laser schlieren system
5. Stability of Hypersonic Boundary Layers over a Compression Corner
Cited by 27 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. Development of the BOLT-2 Roughness Experiment for Flight;Journal of Spacecraft and Rockets;2024-09-03
2. Crossflow Instability on a Swept Fin–Cone with Variable Nose Bluntness in Mach 6 Flow;AIAA Journal;2024-06
3. Görtler Instability and Transition in Compressible Flows;AIAA Journal;2023-12-29
4. Time-resolved heat flux determination from fast-responding temperature-sensitive paint measurement in a shock tunnel using transient in-situ calibration;Measurement Science and Technology;2023-12-15
5. Surface Properties of Double-Fin Generated Shock-Wave/Boundary-Layer Interactions;AIAA Journal;2023-12
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