Transition to turbulence in hypersonic flow over a compression ramp due to upstream forcing
Several transition scenarios are present in a hypersonic compression-ramp flow. In our
previous work (Cao et al., J. Fluid Mech., vol. 941, 2022, p. A8), a complete transition …
previous work (Cao et al., J. Fluid Mech., vol. 941, 2022, p. A8), a complete transition …
Investigation of streamwise streak characteristics over a compression ramp at Mach 4
Experiments of shock wave/boundary layer interactions over a nominally two-dimensional
compression ramp are conducted in a Mach 4 Ludwieg tube tunnel. Measurements of …
compression ramp are conducted in a Mach 4 Ludwieg tube tunnel. Measurements of …
Unsteady Characteristics and Enhanced Determination of Reattachment for Hypersonic Transitional Shock-Wave/Boundary-Layer Interactions
J Davami, TJ Juliano - AIAA AVIATION FORUM AND ASCEND 2024, 2024 - arc.aiaa.org
Infrared thermography and high-speed, high-resolution background-oriented schlieren
(BOS) measurements were made simultaneously on a cone-flare model in the AFOSR …
(BOS) measurements were made simultaneously on a cone-flare model in the AFOSR …
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 …
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 …
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 …