Direct numerical simulations are employed to investigate the flow properties of a shock wave interacting with a turbulent boundary layer at free-stream Mach number M∞ = 2.28 with distinct wall thermal conditions. Adiabatic, heating and cooling wall conditions are considered for a wide range of deflection angles. While heating contributes to increase the extent of the interaction zone, wall cooling turns out to be a good candidate for flow control. The distribution of the Stanton number shows a good agreement with prior experimental studies and confirms the strong heat transfer and complex pattern within the interaction region. Numerical results indicate that the changes in the interaction length due to the wall thermal condition are mainly linked to the incoming boundary layer, which is in agreement with previous experimental studies.

Investigating the effects of non-adiabatic walls on shock/boundary-layer interaction at low reynolds number using direct numerical simulations / Volpiani, P. S.; Larsson, J.; Bernardini, M.. - 19:210059(2018), pp. 14206-14218. (Intervento presentato al convegno 56th AIAA Aerospace Sciences Meeting 2018. AIAA SciTech Forum 2018 tenutosi a Kissimmee, USA) [10.2514/6.2018-1806].

Investigating the effects of non-adiabatic walls on shock/boundary-layer interaction at low reynolds number using direct numerical simulations

Bernardini M.
2018

Abstract

Direct numerical simulations are employed to investigate the flow properties of a shock wave interacting with a turbulent boundary layer at free-stream Mach number M∞ = 2.28 with distinct wall thermal conditions. Adiabatic, heating and cooling wall conditions are considered for a wide range of deflection angles. While heating contributes to increase the extent of the interaction zone, wall cooling turns out to be a good candidate for flow control. The distribution of the Stanton number shows a good agreement with prior experimental studies and confirms the strong heat transfer and complex pattern within the interaction region. Numerical results indicate that the changes in the interaction length due to the wall thermal condition are mainly linked to the incoming boundary layer, which is in agreement with previous experimental studies.
2018
56th AIAA Aerospace Sciences Meeting 2018. AIAA SciTech Forum 2018
shock boundary layer interactions; DNS; non-adiabatic walls
04 Pubblicazione in atti di convegno::04b Atto di convegno in volume
Investigating the effects of non-adiabatic walls on shock/boundary-layer interaction at low reynolds number using direct numerical simulations / Volpiani, P. S.; Larsson, J.; Bernardini, M.. - 19:210059(2018), pp. 14206-14218. (Intervento presentato al convegno 56th AIAA Aerospace Sciences Meeting 2018. AIAA SciTech Forum 2018 tenutosi a Kissimmee, USA) [10.2514/6.2018-1806].
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11573/1317870
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