Transonic film cooling for future aviation gas turbines: A high-fidelity large eddy simulations reference

This work presents a high-resolution large-eddy simulation (LES) database for transonic film cooling representative of modern aero-engine turbine environments. A canonical flat-plate configuration with a single round hole is investigated across six operating conditions that combine low, moderate, and high blowing ratios with two coolant-to-recovery temperature ratios. This parametric sweep isolates momentum- and buoyancy-driven mechanisms that govern jet attachment, plume lift-off, and surface protection. The simulations resolve the incoming turbulent boundary layer and the full jet-in-crossflow interaction, yielding scale-resolved wall-pressure spectra, spanwise energy distributions, and turbulent-kinetic-energy budgets. These diagnostics expose the spectral signatures of plume detachment, the redistribution of turbulent energy between inner and outer shear layers, and the wall-normal migration of peak production within the jet-film interface under transonic conditions. By removing geometric complexity and retaining the essential physics, the resulting dataset provides a rigorous reference for the calibration and assessment of RANS and hybrid RANS-LES closures, wall-model formulations with mass injection, and reduced-order strategies for future gas-turbine aerothermal design. All results are released openly.