Physical insight into a Mach 7.2 compression corner flow

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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 languageEnglish
Title of host publication2018 AIAA Aerospace Sciences Meeting
Place of PublicationReston, VA
DOIs
Publication statusPublished - 8 Jan 2018
EventAIAA SciTech 2018 - Gaylord Palms, Kissimmee, United States
Duration: 8 Jan 201812 Jan 2018
https://scitech.aiaa.org/Register/

Conference

ConferenceAIAA SciTech 2018
CountryUnited States
CityKissimmee
Period8/01/1812/01/18
Internet address

Keywords

  • large eddy simulations
  • shock-boundary layer interaction
  • grid-convergence stud
  • turbulent flow properties

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