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 …
Optical-axis spatial sensitivity of a simulated focused laser differential interferometer
A focused laser differential interferometer (FLDI) simulation was used to study the sensitivity
of the FLDI technique to a variety of factors. The model takes in a series of density fields and …
of the FLDI technique to a variety of factors. The model takes in a series of density fields and …
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 …
Hypersonic transitional boundary-layer profile using a linear-array FLDI
View Video Presentation: https://doi. org/10.2514/6.2023-4253. vid Simultaneous density-
fluctuation measurements were made using a linear array focused laser differential …
fluctuation measurements were made using a linear array focused laser differential …
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 …
Nosetip bluntness effects on a cone-cylinder-flare at mach 6
A cone-cylinder-flare model with sharp and blunt nosetips was tested at the AFRL Mach-6
Ludwieg Tube at a 0\(^{\circ}\) angle of attack. Surface-pressure fluctuation measurements …
Ludwieg Tube at a 0\(^{\circ}\) angle of attack. Surface-pressure fluctuation measurements …
Separation and Transition on a CCF: Experimental Campaigns
EK Benitez, C Caillaud, ZA McDaniel… - AIAA SciTech Forum …, 2024 - ntrs.nasa.gov
Several experimental campaigns have been conducted across a number of Mach-6 facilities
on the hypersonic flow around a CCF (CCF) geometry with a 5° half-angle cone and a 12° …
on the hypersonic flow around a CCF (CCF) geometry with a 5° half-angle cone and a 12° …