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Abstract
High-order implicit Large Eddy Simulations were conducted to study shock-boundary layer interaction around a 33° compression corner at Mach 7.2 and Reynolds number of Reθ = 3,500 based on the momentum thickness. A grid-convergence study was performed to reduce the computational uncertainty and the results were compared with experiments and theoretical predictions. Furthermore, the turbulent flow properties were analysed with respect to the Reynolds normal stress, skewness and flatness, and conclusions were drawn regarding the shock boundary layer interaction behavior.
Original language | English |
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Title of host publication | 2018 AIAA Aerospace Sciences Meeting |
Place of Publication | Reston, VA |
DOIs | |
Publication status | Published - 8 Jan 2018 |
Event | AIAA SciTech 2018 - Gaylord Palms, Kissimmee, United States Duration: 8 Jan 2018 → 12 Jan 2018 https://scitech.aiaa.org/Register/ |
Conference
Conference | AIAA SciTech 2018 |
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Country/Territory | United States |
City | Kissimmee |
Period | 8/01/18 → 12/01/18 |
Internet address |
Keywords
- large eddy simulations
- shock-boundary layer interaction
- grid-convergence stud
- turbulent flow properties
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Dive into the research topics of 'Physical insight into a Mach 7.2 compression corner flow'. Together they form a unique fingerprint.Projects
- 1 Finished
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Shock-induced Turbulence and Acoustic Loading on Aerospace Structures
Drikakis, D. & Kokkinakis, I.
Air Force Office of Scientific Research AFOSR (the)
30/09/15 → 29/09/17
Project: Research