A computer implemented method for the prediction of a surge point of a compressor comprising the following sequence of steps: - generating a plurality of meshes suitable for "Computer Fluid Dynamics" calculation of the compressor, the meshes including: - a compressor inlet mesh representing a stage of inlet guide vanes of the compressor, - at least a compressor rotor stage mesh representing a rotor blade stage of the compressor, - a compressor outlet mesh, representing a plurality of exit guide vanes and an exit nozzle and extending up to a final nozzle exit area of the outlet mesh, - assembling the plurality of meshes (220, 225, 235) to obtain the "Computer Fluid Dynamics" computational domain, - specifying boundary conditions of the computational domain including specifying at least a speed of surfaces representing the rotor blade stage of the compressor, - specifying atmospheric pressure conditions at the final nozzle exit area, - computing through "Computer Fluid Dynamics" calculation the flow along the compressor and calculating compressor inlet mass flow rate and compressor pressure ratio, - checking if a predefined numerical stability limit is reached and, if the numerical stability limit is not reached then: - decreasing dimensions of the final nozzle exit area, - generating again the compressor outlet mesh, - repeating said steps of specifying atmospheric pressure at the final nozzle exit area, said step of computing and said step of checking, - if the numerical stability limit is reached then the method is stopped and a surge point of the compressor is predicted as a point corresponding on a compressor map to the specified speed and to the last calculated value of compressor inlet mass flow rate and compressor pressure ratio. - generating a plurality of meshes suitable for "Computer Fluid Dynamics" calculation of the compressor, the meshes including: - a compressor inlet mesh representing a stage of inlet guide vanes of the compressor, - at least a compressor rotor stage mesh representing a rotor blade stage of the compressor, - a compressor outlet mesh, representing a plurality of exit guide vanes and an exit nozzle and extending up to a final nozzle exit area of the outlet mesh, - assembling the plurality of meshes (220, 225, 235) to obtain the "Computer Fluid Dynamics" computational domain, - specifying boundary conditions of the computational domain including specifying at least a speed of surfaces representing the rotor blade stage of the compressor, - specifying atmospheric pressure conditions at the final nozzle exit area, - computing through "Computer Fluid Dynamics" calculation the flow along the compressor and calculating compressor inlet mass flow rate and compressor pressure ratio, - checking if a predefined numerical stability limit is reached and, if the numerical stability limit is not reached then: - decreasing dimensions of the final nozzle exit area, - generating again the compressor outlet mesh, - repeating said steps of specifying atmospheric pressure at the final nozzle exit area, said step of computing and said step of checking, - if the numerical stability limit is reached then the method is stopped and a surge point of the compressor is predicted as a point corresponding on a compressor map to the specified speed and to the last calculated value of compressor inlet mass flow rate and compressor pressure ratio. - a compressor inlet mesh representing a stage of inlet guide vanes of the compressor, - at least a compressor rotor stage mesh representing a rotor blade stage of the compressor, - a compressor outlet mesh, representing a plurality of exit guide vanes and an exit nozzle and extending up to a final nozzle exit area of the outlet mesh, - assembling the plurality of meshes (220, 225, 235) to obtain the "Computer Fluid Dynamics" computational domain, - specifying boundary conditions of the computational domain including specifying at least a speed of surfaces representing the rotor blade stage of the compressor, - specifying atmospheric pressure conditions at the final nozzle exit area, - computing through "Computer Fluid Dynamics" calculation the flow along the compressor and calculating compressor inlet mass flow rate and compressor pressure ratio, - checking if a predefined numerical stability limit is reached and, if the numerical stability limit is not reached then: - decreasing dimensions of the final nozzle exit area, - generating again the compressor outlet mesh, - repeating said steps of specifying atmospheric pressure at the final nozzle exit area, said step of computing and said step of checking, - decreasing dimensions of the final nozzle exit area, - generating again the compressor outlet mesh, - repeating said steps of specifying atmospheric pressure at the final nozzle exit area, said step of computing and said step of checking, - if the numerical stability limit is reached then the method is stopped and a surge point of the compressor is predicted as a point corresponding on a compressor map to the specified speed and to the last calculated value of compressor inlet mass flow rate and compressor pressure ratio.