Physical insight into a mach 7.2 compression corner flow

Konstantinos Ritos, Ioannis W. Kokkinakis, Dimitris Drikakis

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review


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 languageEnglish
Title of host publicationAIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105241
Publication statusPublished - 2018
Externally publishedYes
EventAIAA Aerospace Sciences Meeting, 2018 - Kissimmee, United States
Duration: 8 Jan 201812 Jan 2018

Publication series

NameAIAA Aerospace Sciences Meeting, 2018


ConferenceAIAA Aerospace Sciences Meeting, 2018
Country/TerritoryUnited States


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