Shock-dominated flow control by plasma array: Pressure analysis including pressure-sensitive paint visualization
This work is focused on the experimental characterization of shock-dominated flow
structures, parameters, and dynamics under control by a filamentary plasma array. Testing …
structures, parameters, and dynamics under control by a filamentary plasma array. Testing …
Global measurements of hypersonic shock-wave/boundary-layer interactions with pressure-sensitive paint
CL Running, TJ Juliano - Experiments in Fluids, 2021 - Springer
Global surface pressure measurements have been carried out on a 7° half-angle circular
cone/flare model at nominally zero angle of attack using pressure-sensitive paint (PSP) …
cone/flare model at nominally zero angle of attack using pressure-sensitive paint (PSP) …
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 …
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 …
Effects of AoA on tangential three-dimensional film cooling of a slender cone
Z Xinhai, Y Shihe, M Qi, D Haolin, N Haibo - Aerospace Science and …, 2022 - Elsevier
A supersonic annular supersonic nozzle was used to protect a slender cone from
aerodynamic heating at angle of attack (AoA). Experiments were carried out in a Mach 6 …
aerodynamic heating at angle of attack (AoA). Experiments were carried out in a Mach 6 …
Characterization of post-shock thermal striations on a cone/flare
SHOCK-WAVE/BOUNDARY-LAYER interactions (SWBLI) observed on an axisymmetric
cone/flare geometry are illustrated in Fig. 1. As the boundary layer grows along the cone …
cone/flare geometry are illustrated in Fig. 1. As the boundary layer grows along the cone …
Global skewness and coherence for hypersonic shock-wave/boundary-layer interactions with pressure-sensitive paint
CL Running, TJ Juliano - Aerospace, 2021 - mdpi.com
The global surface pressure was measured on a 7° half-angle circular cone/flare model at a
nominally zero angle of attack using pressure-sensitive paint (PSP). These experiments …
nominally zero angle of attack using pressure-sensitive paint (PSP). These experiments …
Investigation on transition correlation of conical boundary layer in hypersonic wind tunnel experiments
S Lee, M Duan, G Tu, B Wan, J Chen, X Yuan - Acta Astronautica, 2022 - Elsevier
The wind tunnel experiment is an important approach to studying boundary layer transition.
In this study, the effects of bluntness, unit Reynolds number, and wall temperature ratio on …
In this study, the effects of bluntness, unit Reynolds number, and wall temperature ratio on …
基于温敏漆技术的圆锥高超声速大攻角绕流背风面流动结构实验研究
霍俊杰， 易仕和， 牛海波， 刘小林 - 气体物理, 2022 - qtwl.xml-journal.net
高超声速流动中, 大攻角下圆锥背风面边界层会存在流动分离与再附, 边界层转捩等多种流动
现象, 进而对圆锥表面温度分布产生显著的影响. 为了对这一复杂流动规律及其对表面温升分布 …
现象, 进而对圆锥表面温度分布产生显著的影响. 为了对这一复杂流动规律及其对表面温升分布 …
Analysis of the hypersonic cross-flow instability with experimental wavenumber distributions
HB Yates, MW Tufts, TJ Juliano - Journal of Fluid Mechanics, 2020 - cambridge.org
Stationary cross-flow vortex N-factors were calculated over the surface of a yawed circular
cone using computationally predicted and experimentally observed wavenumber …
cone using computationally predicted and experimentally observed wavenumber …