Hypersonic boundary-layer separation detection with pressure-sensitive paint for a cone at high angle of attack
A measurement technique for identifying lee-side crossflow-induced boundary-layer
separation on a blunt 7^ ∘ 7∘ half-angle circular cone at high angle of attack has been …
separation on a blunt 7^ ∘ 7∘ half-angle circular cone at high angle of attack has been …
Cross-flow transition model predictions of hypersonic transition research vehicle
X Xiang, J Chen, X Yuan, B Wan, Y Zhuang… - Aerospace Science and …, 2022 - Elsevier
Hypersonic transition research vehicle (HyTRV) is a customized lifting body for studying
hypersonic three-dimensional boundary-layer transition on a complex geometry. In this …
hypersonic three-dimensional boundary-layer transition on a complex geometry. In this …
Plasma-actuated flow control of hypersonic crossflow-induced boundary-layer transition
The purpose of this research was to design, fabricate, and test a plasma-based active flow-
control system to accelerate and delay crossflow-induced boundary-layer transition on a …
control system to accelerate and delay crossflow-induced boundary-layer transition on a …
[HTML][HTML] On the mechanism by which nose bluntness suppresses second-mode instability
A Batista, AA Khan, J Kuehl - Theoretical and Applied Mechanics Letters, 2020 - Elsevier
ABSTRACT A physical mechanism by which nose bluntness suppresses second-mode
instability is proposed. Considered are 7 degree half-angle straight cones with nose …
instability is proposed. Considered are 7 degree half-angle straight cones with nose …
HIFiRE-5 boundary-layer transition measured in a Mach-6 quiet tunnel with infrared thermography
TJ Juliano, LA Paquin, MP Borg - AIAA Journal, 2019 - arc.aiaa.org
The principal goal of the Hypersonic International Flight Research Experimentation (HIFiRE)
flight 5 is to measure hypersonic boundary-layer transition on a three-dimensional body …
flight 5 is to measure hypersonic boundary-layer transition on a three-dimensional body …
First and fifth hypersonic international flight research experimentation's flight and ground tests
The Hypersonic International Flight Research Experimentation (HIFiRE) program is a
hypersonic flight-test program executed by the US Air Force Research Laboratory and the …
hypersonic flight-test program executed by the US Air Force Research Laboratory and the …
Nonlinear evolution and breakdown of azimuthally compact crossflow vortex pattern over a yawed cone
I. Introduction oundary layer transition from the laminar to a turbulent state is known to have
a major impact on the design and performance of hypersonic flight vehicles. When the …
a major impact on the design and performance of hypersonic flight vehicles. When the …
7° 尖锥高超声速边界层转捩红外测量实验
陈久芬， 凌岗， 张庆虎， 解福田， 许晓斌， 张毅锋 - 实验流体力学, 2020 - syltlx.com
为了推动高超声速边界层转捩研究的深入开展, 给边界层转捩机理研究, 物理模型验证,
转捩数据库构建和转捩天地相关性的建立等提供基础风洞实验数据, 在中国空气动力研究与发展 …
转捩数据库构建和转捩天地相关性的建立等提供基础风洞实验数据, 在中国空气动力研究与发展 …
On energy redistribution for the nonlinear parabolized stability equations method
We identify and quantify a seemingly overlook mechanism for energy transfer between
adjacent frequency disturbances in the Nonlinear Parabolized Stability Equations method …
adjacent frequency disturbances in the Nonlinear Parabolized Stability Equations method …
升力体外形高超声速边界层转捩红外测量实验
陈久芬， 徐洋， 蒋万秋， 凌岗， 段茂昌， 张毅锋 - 实验流体力学, 2024 - syltlx.com
在常规高超声速风洞中, 开展了针对升力体模型的边界层转捩红外测量实验,
研究了不同单位雷诺数和马赫数对升力体边界层转捩的影响规律, 并与e N 方法计算结果进行了 …
研究了不同单位雷诺数和马赫数对升力体边界层转捩的影响规律, 并与e N 方法计算结果进行了 …