Large-Eddy Simulation of Supersonic Film Cooling at Incident Shock-Wave Interaction
Martin Konopka (),
Matthias Meinke and
Wolfgang Schröder
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Martin Konopka: RWTH Aachen University, Institute of Aerodynamics
Matthias Meinke: RWTH Aachen University, Institute of Aerodynamics
Wolfgang Schröder: RWTH Aachen University, Institute of Aerodynamics
A chapter in High Performance Computing in Science and Engineering ‘12, 2013, pp 295-310 from Springer
Abstract:
Abstract The impact of shock waves on supersonic cooling films is studied using large-eddy simulations (LES). A laminar cooling film is injected through a slot at a Mach number Ma i =1.8 into a fully turbulent boundary layer at a freestream Mach number Ma ∞ =2.44. The cooling film is disturbed by oblique shock waves at deflection angles of 5∘ and 8∘ at two downstream positions of the slot. At shock impingement close to the slot, i.e., within the potential-core region, at a flow deflection of 5∘, a cooling effectiveness decrease of 33% occurs downstream of the separation bubble compared to a configuration without shock impingement. If the same shock impinges further downstream upon the boundary-layer region, the decrease is only 17%. The stronger 8∘ shock wave at the further downstream impingement position leads to a maximum decrease of 33%. The current report presents a concise version of Konopka etal. (4th European conference for aerospace sciences, 2011).
Keywords: Reynolds Average Navier Stoke; Reynolds Average Navier Stoke; Separation Bubble; Film Cool; Cool Flow (search for similar items in EconPapers)
Date: 2013
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Persistent link: https://EconPapers.repec.org/RePEc:spr:sprchp:978-3-642-33374-3_22
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DOI: 10.1007/978-3-642-33374-3_22
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