4TH EUROPEAN CONFERENCE FOR AEROSPACE SCIENCES Influence of a Favorable Streamwise Pressure Gradient on Laminar Film Cooling at Mach 2.67
نویسندگان
چکیده
Direct numerical simulations are used to investigate the method of film cooling in a laminar flat-plate Mach-2.67 boundary layer. Air is employed as mean-flow and coolant gas and is introduced into the boundary layer through one row of holes by means of a modeled blowing approach. The effects of a favorable streamwise pressure gradient are investigated for two different blowing rates and an adiabatic-wall boundary condition. It is shown that a favorable streamwise pressure gradient has a beneficial influence on the cooling effectiveness, mainly due to the higher streamwise velocity close to the wall.
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