Abstract: A method and apparatus for predicting the onset of stall in an axial flow compressor and stabilizing stall so as to achieve the maximum pressure rise to the combustor. Stall in an axial flow compressor is predicted by obtaining pressure or axial velocity measurements at a plurality of circumferential angles around a compressor stage, fourier transforming the measurements with respect to the circumferential angles to obtain a time history of the zeroth, first and higher modes, and determining amplitude gain at twice the rotor frequency of the transfer function from the product of the zeroth and first modes to the first mode, with an increase in amplitude gain depicting a right skewed compressor going into stall and a decrease in amplitude gain depicting a left skewed compressor going into stall.