Effect of Angle of Attack on Separation Bubble Instability and Transition on a Cone-Slice-Ramp in Mach-6 Quiet Flow
AA Francis, JS Jewell - AIAA SCITECH 2024 Forum, 2024 - arc.aiaa.org
The Boeing/AFOSR Mach-6 Quiet Tunnel (BAM6QT) at Purdue University was used to
investigate the effect of angle of attack on three-dimensional compression-induced shock …
investigate the effect of angle of attack on three-dimensional compression-induced shock …
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 …
Study of Bluntness-Induced Elongated Structures in Hypersonic Flow over a 7 degree Circular Cone
View Video Presentation: https://doi. org/10.2514/6.2023-0290. vid Bluntness effects have
been investigated on a 7◦ half angle cone with removable tips at zero angle of attack in …
been investigated on a 7◦ half angle cone with removable tips at zero angle of attack in …
Design of a cone-cylinder-flare configuration for hypersonic boundary-layer stability analyses and measurements with attached and separated flows
S Esquieu, SP Schneider, EK Benitez… - AERO 2023-The 3AF …, 2023 - hal.science
The stability of hypersonic boundary-layer over axisymmetric cone-cylinder-flare
configurations at Mach 6 and zero degree angle of attack is investigated for different …
configurations at Mach 6 and zero degree angle of attack is investigated for different …
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 cone-cylinder-flare: computational investigations
C Caillaud, S Esquieu, A Scholten, P Paredes… - AIAA SCITECH 2024 …, 2024 - arc.aiaa.org
Base flow computation and stability analysis were conducted for hypersonic flow over a
cone-cylinder-flare (CCF) geometry for conditions that correspond to the experimental runs …
cone-cylinder-flare (CCF) geometry for conditions that correspond to the experimental runs …
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 …
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° …
Unraveling Flow Transition: Experimental Insights into Mach, Reynolds, and Bluntness Variations on a Cone-Cylinder Flare Model
T Ince-Ingram, AR Berger, J Gustavsson… - AIAA AVIATION FORUM …, 2024 - arc.aiaa.org
The objective of this study is to map the Mach number, Reynolds number, and bluntness
conditions in which separation bubbles over the compression region are observed in the …
conditions in which separation bubbles over the compression region are observed in the …