An experimental test campaign has been conducted by Safran and ONERA in order to generate a database on an annular effusion cooling system. Different effusion cooling patterns have been tested in various flow field conditions, representative of those encountered in real aeronautical combustors in terms of Reynolds number in the perforations, blowing ratio and momentum ratio. This paper presents the numerical modelling of three tests conducted in the same flow field condition for three effusion cooling patterns, featuring different compound angles: 0°, 45° and 90°. Comparisons are made between the experimental wall temperature measured by infrared thermography and the associated RANS simulations. The cooling efficiency is overestimated by RANS simulations, especially for high compound angle values. Comparisons of the cooling film development mechanisms between these three simulations are presented by analyzing the temperature field close to the multiperforated wall.