In this numerical study film cooling flows are analyzed. To be more precise, two categories of flows are investigated each of which undergoes an external pressure gradient. The first is the subsonic flow over the rear part of turbine blades at misaligned flow or over the rear part of high-lift turbine blades and the second problem is the cooling flow in a supersonic combustion ramjet (scramjet). The cooling film interactions are characterized by analyzing the instantaneous flow field, mean flow field, and turbulence statistics. Additionally the simulations are extensively validated by experimental data.