TY - GEN
T1 - DNS and Experimental Study of Shock Wave/Turbulent Boundary Layer Interaction over a Mach 6.32 Hollow-Cylinder/Flare
AU - Roy, Dhiman
AU - Schuabb, Mateus
AU - Aultman, Matthew
AU - Duan, Lian
AU - Segall, Ben
AU - Keenoy, Tim
AU - Kokinakos, Jaden
AU - Parziale, Nicholaus
AU - Hameed, Ahsan
N1 - Publisher Copyright:
© 2025, American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
PY - 2025
Y1 - 2025
N2 - This study presents a combined direct numerical simulation (DNS) and experimental investigation of shock wave/turbulent boundary layer interaction (SBLI) over a hollow-cylinder/flare (HCF) configuration at Mach 6.32, with a flare angle of 34◦. The DNS replicates conditions from the Stevens Shock Tunnel, with matched freestream and wall temperature conditions (Reu∞/m = 13.86 × 106, Tw/Tr = 0.54). Detailed comparisons of DNS against experiments are made. Upstream of the interaction, the simulation shows excellent agreement in mean velocity profiles and Morkovin-scaled turbulence intensities with Stevens’ experiment, as well as with other flat-plate data in the literature. Within the flare-induced SBLI region, the DNS captures key features of separation, reattachment, and shock-induced surface loading. Instantaneous schlieren images from the DNS closely match the experimental schlieren, capturing the structure and dynamics of shock motion and the evolving separation bubble. Additionally, wall pressure signals from the DNS align well with Kulite measurements, with improved agreement observed after applying low-pass filtering to account for sensor’s effective bandwidth.
AB - This study presents a combined direct numerical simulation (DNS) and experimental investigation of shock wave/turbulent boundary layer interaction (SBLI) over a hollow-cylinder/flare (HCF) configuration at Mach 6.32, with a flare angle of 34◦. The DNS replicates conditions from the Stevens Shock Tunnel, with matched freestream and wall temperature conditions (Reu∞/m = 13.86 × 106, Tw/Tr = 0.54). Detailed comparisons of DNS against experiments are made. Upstream of the interaction, the simulation shows excellent agreement in mean velocity profiles and Morkovin-scaled turbulence intensities with Stevens’ experiment, as well as with other flat-plate data in the literature. Within the flare-induced SBLI region, the DNS captures key features of separation, reattachment, and shock-induced surface loading. Instantaneous schlieren images from the DNS closely match the experimental schlieren, capturing the structure and dynamics of shock motion and the evolving separation bubble. Additionally, wall pressure signals from the DNS align well with Kulite measurements, with improved agreement observed after applying low-pass filtering to account for sensor’s effective bandwidth.
KW - Boundary Layer Interaction
KW - Freestream Mach Number
KW - Incompressible Flow
KW - Kinematic Viscosity
KW - Reynolds Averaged Navier Stokes
KW - Sensors
KW - Shock Waves
KW - Turbulence Intensity
KW - Wall Temperature
KW - Weighted Essentially Non Oscillatory
UR - https://www.scopus.com/pages/publications/105018090166
UR - https://www.scopus.com/pages/publications/105018090166#tab=citedBy
U2 - 10.2514/6.2025-3529
DO - 10.2514/6.2025-3529
M3 - Conference contribution
AN - SCOPUS:105018090166
SN - 9781624107382
T3 - AIAA Aviation Forum and ASCEND, 2025
BT - AIAA AVIATION FORUM AND ASCEND, 2025
T2 - AIAA AVIATION FORUM AND ASCEND, 2025
Y2 - 21 July 2025 through 25 July 2025
ER -