Abstract: This invention relates to a method and apparatus for obtaining the angle of attack of an aircraft developed as a result of an appropriate processing of the vertical speed, the airspeed, and the pitch attitude of the aircraft. The latter involves resolving the inverse sine of the vertical speed signal over the airspeed signal, and subsequently differentially combining the end product of the inverse sine computation and the chord line angle signal. The air speed signal is corrected by a corrective network which receives a feedback signal proportional to the angle of attack as well as a signal proportional to drift angle.