Abstract: Methods and apparatus for predicting airfoil stall for an aircraft having a control surface. Measurements of forces or moments acting upon an integrated span of the control surface are sensed over a period of time to provided unsteady data. The unsteady data is filtered to remove structural frequencies and input to at least one stall warning detection function, and an output is received. Each of the stall warning detection functions identifies an angle-of-attack that is approximately within a predetermined number of degrees of stall when the received output reaches a threshold. The received output is compared to the threshold to determine whether an angle-of-attack exists that is near stall.