This master’s thesis presents an investigation of end wall and cavity effect on probes reading in a turbine rig environment. Probe measurements in aeronautical engine can be challenging due to potential errors, which may affect the accuracy of crucial data used to evaluate engine performance. This could lead to misinterpretations that compromise operational efficiency and aerodynamic projects. Firstly, a CAD model of five-hole probe was developed with Siemens- NX following the real probe used by Avio Aero GE in the test rig. Since experimental calibration, applied to data reduction of CAD probe, leads to deviation; a numerical calibration was carried out.