Measurements of an axisymmetric hypersonic shear-layer instability on a cone-cylinder-flare in quiet flow
Instabilities generated in Mach-6 quiet flow about an axisymmetric cone-cylinder-flare
geometry with a 5∘ half-angle sharp cone were studied in the Boeing/AFOSR Mach-6 Quiet …
geometry with a 5∘ half-angle sharp cone were studied in the Boeing/AFOSR Mach-6 Quiet …
Transitional shockwave/boundary layer interaction experiments in the R2Ch blowdown wind tunnel
Transitional shockwave/boundary layer interactions (SBLI) are studied experimentally.
Experiments are conducted on a hollow-cylinder flare model in the R2Ch blowdown facility …
Experiments are conducted on a hollow-cylinder flare model in the R2Ch blowdown facility …
Boundary-layer instabilities over a cone–cylinder–flare model at Mach 6
P Paredes, A Scholten, MM Choudhari, F Li… - AIAA Journal, 2022 - arc.aiaa.org
Computations are performed to investigate the convective and global boundary-layer
instabilities over a sharp cone–cylinder–flare model at zero-degree angle of attack. The …
instabilities over a sharp cone–cylinder–flare model at zero-degree angle of attack. The …
Separation and transition on a cone-cylinder-flare: Experimental campaigns
Several experimental campaigns have been conducted across a number of Mach-6 facilities
on the hypersonic flow around a cone-cylinder-flare (CCF) geometry with a 5 ^∘ half-angle …
on the hypersonic flow around a cone-cylinder-flare (CCF) geometry with a 5 ^∘ half-angle …
Instability measurements on two cone-cylinder-flares at Mach 6
EK Benitez - 2021 - search.proquest.com
This research focuses on measurements of a convective shear-layer instability seen
naturally in quiet hypersonic flow. Experiments were carried out in the Boeing/AFOSR Mach …
naturally in quiet hypersonic flow. Experiments were carried out in the Boeing/AFOSR Mach …
Measurements on a blunt cone-cylinder-flare at mach 6
View Video Presentation: https://doi. org/10.2514/6.2023-1245. vid A blunt cone-cylinder-
flare model was tested at the AFRL Mach-6 Ludwieg Tube at 0-degree angle of attack …
flare model was tested at the AFRL Mach-6 Ludwieg Tube at 0-degree angle of attack …
Nonlinear evolution of instabilities in a laminar separation bubble at hypersonic Mach number
F Li, MM Choudhari, P Paredes… - AIAA AVIATION 2022 …, 2022 - arc.aiaa.org
View Video Presentation: https://doi. org/10.2514/6.2022-3855. vid The development of both
convective stationary perturbation as well as global instabilities in the vicinity of a laminar …
convective stationary perturbation as well as global instabilities in the vicinity of a laminar …
High-Speed Schlieren Visualization in Mach-6 Quiet Tunnel
B Price, Z McDaniel, SA Miller, S Overpeck… - AIAA SCITECH 2022 …, 2022 - arc.aiaa.org
View Video Presentation: https://doi. org/10.2514/6.2022-1672. vid The Boeing/AFOSR
Mach-6 Quiet Tunnel (BAM6QT) at Purdue has lacked optical access for schlieren …
Mach-6 Quiet Tunnel (BAM6QT) at Purdue has lacked optical access for schlieren …
Nonlinear evolution of instabilities in a laminar separation bubble at hypersonic speeds
F Li, M Choudhari, P Paredes, A Scholten - AIAA Journal, 2024 - arc.aiaa.org
The development of both convective stationary perturbation and global instabilities in the
vicinity of a laminar separation bubble above an axisymmetric compression corner in …
vicinity of a laminar separation bubble above an axisymmetric compression corner in …
Instability and transition onset downstream of an axisymmetric separation bubble with sharp and blunt nosetips
View Video Presentation: https://doi. org/10.2514/6.2023-3702. vid A cone-cylinder-flare
model was tested at the Boeing/AFOSR Mach-6 Quiet Tunnel at 0-deg angle of attack …
model was tested at the Boeing/AFOSR Mach-6 Quiet Tunnel at 0-deg angle of attack …