Numerical investigation of shock/film-cooling interaction

K. Ozawa, S. Loosen, M. Albers, P. S. Meysonnat, M. Meinke, W. Schröder, S. Obayashi

Research output: Contribution to conferencePaperpeer-review


In this numerical study, a film-cooling flow with shock-wave interaction is analyzed using large-eddy simulation (LES). A laminar cooling film at an injection Mach number of Mai = 1.8 is injected through a slot into a fully turbulent boundary layer at a freestream Mach number of Ma1 = 2.44. An oblique shock, generated by a flow deflection of β = 5∘ or 8∘, impinges upon the cooling film within the potential-core region. At a deflection angle of β = 5∘, the cooling effectiveness downstream the shock impingement is decreased by 4.6% compared to the undisturbed flow configuration. A flow deflection of β = 8∘ leads to a decrease in cooling effectiveness of 13.4%. The separation bubble at the shock impingement position causes a strong negative peak of the Reynolds shear stress near the wall. With increasing shock strength, the separation bubble significantly grows in size. The separation length of the strong shock configuration is increased by a factor of 4.6 compared to the weaker shock configuration.

Original languageEnglish
Publication statusPublished - 2018
Event10th International Conference on Computational Fluid Dynamics, ICCFD 2018 - Barcelona, Spain
Duration: 2018 Jul 92018 Jul 13


Conference10th International Conference on Computational Fluid Dynamics, ICCFD 2018


  • LES
  • Shock-Cooling Film Interaction
  • Slot-Film Cooling
  • Supersonic Flow


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