Numerical investigations of the linear and nonlinear transition stages for a hollow cylinder flare at Mach 5
V Tsakagiannis, C Hader, HF Fasel - AIAA AVIATION FORUM AND …, 2024 - arc.aiaa.org
Direct numerical simulations (DNS) were carried out in order to investigate the linear and
nonlinear transition stages for a shock boundary layer interaction (SBLI) on a hollow cylinder …
nonlinear transition stages for a shock boundary layer interaction (SBLI) on a hollow cylinder …
Progress on Quantitative Infrared Thermography at the NASA Langley Aerothermodynamic Laboratory
FD Turbeville, C Broslawski… - AIAA AVIATION FORUM …, 2024 - arc.aiaa.org
A quantitative infrared thermography technique is being developed for accurate and
highresolution measurements of surface temperature and heat flux in the hypersonic wind …
highresolution measurements of surface temperature and heat flux in the hypersonic wind …
Scaling and Transition Effects on Hollow-Cylinder/Flare SBLIs in Wind Tunnel Environments
A comprehensive investigation into the flow over a Hollow-Cylinder/Flare (HCF) has been
conducted at Mach 5 with Re_L≈ 11× 10^ 5 and a flare deflection θ= 15 deg. Experiments …
conducted at Mach 5 with Re_L≈ 11× 10^ 5 and a flare deflection θ= 15 deg. Experiments …
Numerical investigations of laminar-turbulent transition for a hollow cylinder flare at Mach 5
V Tsakagiannis, C Hader, HF Fasel - AIAA SCITECH 2024 Forum, 2024 - arc.aiaa.org
Numerical investigations were carried in order to investigate the transitional shock boundary-
layer interaction on a hollow cylinder flare geometry at Mach 5. The influence of the flare …
layer interaction on a hollow cylinder flare geometry at Mach 5. The influence of the flare …
Numerical Investigations of the Linear Stability Regime for a Separation Bubble on an Axisymmetric Compression Ramp at Mach 5
V Tsakagiannis, C Hader, H Fasel - AIAA SCITECH 2025 Forum, 2025 - arc.aiaa.org
Numerical investigations were carried in order to investigate the transitional shock boundary-
layer interaction (SBLI) on a hollow cylinder flare geometry at Mach 5. The geometry and …
layer interaction (SBLI) on a hollow cylinder flare geometry at Mach 5. The geometry and …
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 …
Visualization of Aerodynamic Heating Caused by Shock Incident on Inclined Flat Plate in Mach 10 Hypersonic Flow
M Taguchi, M Kashitani - AIAA SCITECH 2025 Forum, 2025 - arc.aiaa.org
This study investigated the aerodynamic heating effects caused by Shock/Boundary Layer
Interaction (S/BLI) when an oblique shock impinges on an inclined hypersonic flat plate. The …
Interaction (S/BLI) when an oblique shock impinges on an inclined hypersonic flat plate. The …
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 …