Experimental measurements and numerical investigations of boundary-layer instabilities on a Mach 5 hollow cylinder
JJ Flood, C Hader, A Skora, HF Fasel… - AIAA SciTech 2023 …, 2023 - arc.aiaa.org
View Video Presentation: https://doi. org/10.2514/6.2023-1247. vid Experiments were
performed on a hollow cylinder model at Mach 4.82 in an effort to understand the physics …
performed on a hollow cylinder model at Mach 4.82 in an effort to understand the physics …
Transition and Separation Over a Hollow Cylinder-Flare at Mach 5
Hypersonic laminar and transitional Shock Boundary Layer Interaction (SBLI) over a 𝜃= 8
degree hollow cylinder-flare model is characterized in a Mach 4.8 flow at unit Reynolds …
degree hollow cylinder-flare model is characterized in a Mach 4.8 flow at unit Reynolds …
Structure and Unsteadiness of Fin-Induced Transitional Shock Boundary Layer Interactions at Mach 5
A Plummer, S Padmanabhan, JA Threadgill… - AIAA SCITECH 2025 …, 2025 - arc.aiaa.org
Fin-induced Shock Boundary Layer Interactions (SBLIs) are studied on a hollow cylinder at
Mach 5 over a range of Reynolds numbers from 1.27*10^6 to 4.90*10^6. The incoming …
Mach 5 over a range of Reynolds numbers from 1.27*10^6 to 4.90*10^6. The incoming …
Experimental investigation of transition on a 7-degree cone at Mach 5
A Skora, SA Craig - AIAA SCITECH 2024 Forum, 2024 - arc.aiaa.org
In order to conduct advanced studies investigating variables such as bluntness or angle of
attack, a baseline case must be established. An experimental investigation of transition on a …
attack, a baseline case must be established. An experimental investigation of transition on a …
Transitional Fin-Induced Shock Boundary Layer Interactions on a Hollow Cylinder at Mach 5
AE Plummer, S Padmanabhan, A Singh… - AIAA AVIATION 2023 …, 2023 - arc.aiaa.org
View Video Presentation: https://doi. org/10.2514/6.2023-3700. vid Fin-induced Shock
Boundary Layer Interactions (SBLIs) are investigated on a hollow cylinder at Mach 5 across …
Boundary Layer Interactions (SBLIs) are investigated on a hollow cylinder at Mach 5 across …
Transitional Shock Wave Boundary Layer Interactions and Surface Heat Transfer on a Hollow-Cylinder/Flare at Mach 5
AHR Garcia - 2024 - search.proquest.com
A hollow-cylinder model with a 15◦ half-angle flare is tested at Mach 5 for five different
Reynolds numbers ranging from 4.10× 10 5< Re L< 1.62× 10 6. The laminar boundary layer …
Reynolds numbers ranging from 4.10× 10 5< Re L< 1.62× 10 6. The laminar boundary layer …