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- W2108526571 abstract "To analyze lm cooling in supersonic combustion ramjets (Scramjets) Large-eddy simulations are performed. The lm cooling ow is injected into a fully turbulent boundary layer through a slot parallel to a Ma = 2:44 main stream. The injection Mach numbers are Mai = 1:8 and Mai = 2:2 at laminar and turbulent injection conditions, respectively. The blowing rate M and the total temperature ratio TR are kept constant at both injection conditions. For these injection conditions, the adiabatic cooling e ectiveness is investigated. The numerical results for the laminar injection are in good agreement with the measured adiabatic cooling e ectiveness. The turbulent injection condition leads to an increased mixing between the cooling ow and the main stream which results in an approx. 7 % reduction of adiabatic cooling e ectiveness values compared to the laminar injection condition." @default.
- W2108526571 created "2016-06-24" @default.
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- W2108526571 date "2011-04-11" @default.
- W2108526571 modified "2023-09-28" @default.
- W2108526571 title "Large-Eddy Simulation of Supersonic Film Cooling at Laminar and Turbulent Injection" @default.
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- W2108526571 doi "https://doi.org/10.2514/6.2011-2250" @default.
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