The main aim of this master thesis is to verify and validate a CFD code that simulate a resonance igniter for rocket engines applications during the transient heat-up phase and using air as working fluid, in order to establish if it is capable to reproduce the experimental results and the main flow features. This analysis is motivated by the urgent need of developing a reliable and safe igniter for rockets upper stages driven by green propellants, not hypergolic because they are hydrazine free, since this material has been classified as toxic. Thanks to the high reliablity this ignition technology is particularly suitable for satellite propulsion systems with long mission durations and a high number of ignitions.