TY - GEN
T1 - Flow structure and heat transfer characterization of a blunt-fin-induced shock-wave/laminar boundary-layer interaction
AU - Maldonado, Jorge Castro
AU - Threadgill, James A.S.
AU - Craig, Stuart A.
AU - Little, Jesse C.
AU - Wernz, Stefan
N1 - Funding Information:
The authors would like to acknowledge Raytheon Missiles & Defense for their invaluable support, and Dr. Tianshu Liu for his help in implementing the heat flux method [47].
Publisher Copyright:
© 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2021
Y1 - 2021
N2 - A combined experimental and numerical investigation of a blunt-fin-induced shock-wave/ laminar boundary-layer interaction (SBLI) has been conducted at a nominal Mach number of 4. Two blunt fins with a leading-edge diameter of 9.525 mm (3/8”) and sweep angles of 0 and 45 degrees were tested on a flat plate with unit Reynolds number 4.3×106 m−1 (Rex = 2.7×105 ). The unswept fin produces significant separation extending x/D ≈ −5.5 upstream of the fin leading edge. Mach number contours indicate two horseshoe vortices wrapping around the unswept fin base. The swept fin SBLI features are subdued in comparison, but qualitatively similar, with evidence of horseshoe vortices also present. Temperature sensitive paint (TSP) was employed to investigate the near-wall flow structure and estimate surface heat flux. Prominent features include various reattachment lines associated with vortices in the separated region, as well as shock-shock interactions and shear-layer impingement on the fin leading edge. Increasing the sweep angle altered the flow topology considerably, including the location and magnitude of maximum heat flux. The surface distribution of Stanton numbers are derived, demonstrating complex interactions with a rich set of flow physics to be investigated in future work. Amongst other findings, the influence of sweep has a moderate impact on peak heat transfers with Stanton numbers reaching 0.022 and 0.035 for the swept and unswept fins, respectively.
AB - A combined experimental and numerical investigation of a blunt-fin-induced shock-wave/ laminar boundary-layer interaction (SBLI) has been conducted at a nominal Mach number of 4. Two blunt fins with a leading-edge diameter of 9.525 mm (3/8”) and sweep angles of 0 and 45 degrees were tested on a flat plate with unit Reynolds number 4.3×106 m−1 (Rex = 2.7×105 ). The unswept fin produces significant separation extending x/D ≈ −5.5 upstream of the fin leading edge. Mach number contours indicate two horseshoe vortices wrapping around the unswept fin base. The swept fin SBLI features are subdued in comparison, but qualitatively similar, with evidence of horseshoe vortices also present. Temperature sensitive paint (TSP) was employed to investigate the near-wall flow structure and estimate surface heat flux. Prominent features include various reattachment lines associated with vortices in the separated region, as well as shock-shock interactions and shear-layer impingement on the fin leading edge. Increasing the sweep angle altered the flow topology considerably, including the location and magnitude of maximum heat flux. The surface distribution of Stanton numbers are derived, demonstrating complex interactions with a rich set of flow physics to be investigated in future work. Amongst other findings, the influence of sweep has a moderate impact on peak heat transfers with Stanton numbers reaching 0.022 and 0.035 for the swept and unswept fins, respectively.
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M3 - Conference contribution
AN - SCOPUS:85100298201
SN - 9781624106095
T3 - AIAA Scitech 2021 Forum
SP - 1
EP - 19
BT - AIAA Scitech 2021 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021
Y2 - 11 January 2021 through 15 January 2021
ER -