Large-eddy simulation of high mach number film cooling with shock-wave interaction

Abstract

The impact of shock waves on supersonic cooling ¦lms is studied using large-eddy simulations (LES). A laminar cooling ¦lm 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 ¦lm is disturbed by oblique shock waves at de §ection 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 §ow de §ection of 5 • , a cooling e¨ectiveness decrease of 33% occurs downstream of the separation bubble compared to a con¦guration without shock impingement. If the same shock impinges further downstream upon the boundary-layer region, the decrease is only 17%. The stronger 8 degree shock wave at the further downstream impingement position leads to a maximum decrease of 33%.