Abstract: The present invention relates to a method and device for predicting the instability of an axial compressor, which is applicable to the aerospace and industrial field, specifically to the field of one- or multi-stage axial compressors. The invention relates to a method and a device for predicting the instability of an axial compressor which allows protecting said compressor from the instabilities of devices of this type. The present invention could be used in all those products requiring the use of said compressors, such as aircraft engines, turbofans, turboshafts, or turboprops in the aerospace field, gas turbines in the energy field, air conditioning systems in the civil field, and gas compression systems in the chemical or oil industry.