Title of Paper:NUMERICAL INVESTIGATION OF HEAT TRANSFER IN FILM LAYER UNDER SUPERSONIC CONDITION OF CONVERGENT-DIVERGENT TRANSITION

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Journal:THERMAL SCIENCE

Abstract:The distribution of film cooling effectiveness in supersonic mainstream of circle-rectangular Convergent-Divergent transition has been numerically investigated under different pressure ratios. The shock wave exerted superior influence on
film cooling. In supersonic main flow, extra compression waves formed in upstream
of the film holes, resulted by the obstruction of the multiple cooling jets. This exerted extra pressure to the boundary-layer, induced adverse pressure gradient, and
led to weakening of the film flow attachment ability and decreasing of local cooling
effectiveness. Bow oblique shock wave occurred in front of holes, the two oblique
bow shaped low pressure zones formed on both sides of the hole, and low cooling effectiveness zones appeared accordingly. The inefficient region at the leading
edge of the hole destroyed the film developing between holes, decreased the cooling effectiveness accumulation in the rear part. The decrease of hole incline angle
caused an

Document Type:J

Translation or Not:no