Instability and transition onset downstream of a laminar separation bubble at Mach 6
Instability measurements of an axisymmetric, laminar separation bubble were made over a
sharp cone-cylinder-flare with a flare angle under hypersonic quiet flow. Two distinct …
sharp cone-cylinder-flare with a flare angle under hypersonic quiet flow. Two distinct …
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 …
Instability measurements on an axisymmetric separation bubble at Mach 6
EK Benitez, S Esquieu, JS Jewell… - Aiaa aviation 2020 …, 2020 - arc.aiaa.org
An axisymmetric sharp cone-cylinder-flare model was tested in the Boeing/AFOSR Mach 6
Quiet Tunnel (BAM6QT) at 0.0-degree angle of attack. Heat transfer and surface-pressure …
Quiet Tunnel (BAM6QT) at 0.0-degree angle of attack. Heat transfer and surface-pressure …
Response of hypersonic compression corner flow to upstream disturbances
Hypersonic flow over a two-dimensional compression corner is investigated using
computational fluid dynamics and global resolvent analysis in this study, which is a …
computational fluid dynamics and global resolvent analysis in this study, which is a …
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 bubble variation due to small angles of attack for an axisymmetric model at mach 6
EK Benitez, JS Jewell, SP Schneider - AIAA Scitech 2021 Forum, 2021 - arc.aiaa.org
View Video Presentation: https://doi. org/10.2514/6.2021-0245. vid The Boeing/AFOSR
Mach 6 Quiet Tunnel (BAM6QT) at Purdue University was used to test a sharp cone-cylinder …
Mach 6 Quiet Tunnel (BAM6QT) at Purdue University was used to test a sharp cone-cylinder …
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 …
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 …
Femtosecond laser electronic excitation tagging velocimetry in a Mach six quiet tunnel
EXPERIMENTS to demonstrate and evaluate the use of femto-second laser electronic
excitation tagging (FLEET) velocimetry [1, 2] in the Boeing/Air Force Office of Scientific …
excitation tagging (FLEET) velocimetry [1, 2] in the Boeing/Air Force Office of Scientific …