An aircraft airflow sensor probe comprising: an airflow assembly (53, 316) configured to sense a direction of local airflow outside an aircraft; a shaft (14, 18) configured to rotatably hold the airflow assembly (53, 316) and allow rotational movement of the airflow assembly (53, 316); a motor connected to the shaft (14, 18) and configured to generate a torque to damp the rotational movement of the shaft (14, 18) as well as the airflow assembly (53, 316); the aircraft airflow sensor probe further characterized in comprising: an angle of attack processor configured to control the motor to generate the torque to damp the rotational movement of the shaft (14, 18) as well as the airflow assembly (53, 316) based on at least one of the following: a static air pressure, an airspeed, a pressure differential between an upper side of the airflow assembly and a lower side of the airflow assembly, a rate of change of an angle of attack, an angle of attack, and an ambient temperature; and a sensor configured to sense a position of the airflow assembly (53, 316) and provide the position of the airflow assembly to the angle of attack processor, wherein the airflow assembly (53, 316) comprises one of the following: a vane assembly configured to sense a direction of local airflow outside an aircraft and a cone assembly configured to sense a direction of local airflow outside an aircraft. an airflow assembly (53, 316) configured to sense a direction of local airflow outside an aircraft; a shaft (14, 18) configured to rotatably hold the airflow assembly (53, 316) and allow rotational movement of the airflow assembly (53, 316); a motor connected to the shaft (14, 18) and configured to generate a torque to damp the rotational movement of the shaft (14, 18) as well as the airflow assembly (53, 316); the aircraft airflow sensor probe further characterized in comprising: an angle of attack processor configured to control the motor to generate the torque to damp the rotational movement of the shaft (14, 18) as well as the airflow assembly (53, 316) based on at least one of the following: a static air pressure, an airspeed, a pressure differential between an upper side of the airflow assembly and a lower side of the airflow assembly, a rate of change of an angle of attack, an angle of attack, and an ambient temperature; and a sensor configured to sense a position of the airflow assembly (53, 316) and provide the position of the airflow assembly to the angle of attack processor, wherein the airflow assembly (53, 316) comprises one of the following: a vane assembly configured to sense a direction of local airflow outside an aircraft and a cone assembly configured to sense a direction of local airflow outside an aircraft. an angle of attack processor configured to control the motor to generate the torque to damp the rotational movement of the shaft (14, 18) as well as the airflow assembly (53, 316) based on at least one of the following: a static air pressure, an airspeed, a pressure differential between an upper side of the airflow assembly and a lower side of the airflow assembly, a rate of change of an angle of attack, an angle of attack, and an ambient temperature; and a sensor configured to sense a position of the airflow assembly (53, 316) and provide the position of the airflow assembly to the angle of attack processor, wherein the airflow assembly (53, 316) comprises one of the following: a vane assembly configured to sense a direction of local airflow outside an aircraft and a cone assembly configured to sense a direction of local airflow outside an aircraft.