The utility model relates to a wing tip antenna radome of certain type of airplane and particularly relates to an integrated type airplane wing tip antenna radome contour, belonging to the field of overall pneumatic contour design. As the contour dimension of an additionally arranged antenna is large, by adopting a streamline design method of integration transition between antenna radome contour and an airplane wing in the distribution design of the antenna radome, the airflow can be avoided from separating when flowing through the antenna radome, so as to improve the field of air flow; on the premise of meeting the usage requirement of a task system, the contour dimension of the antenna radome can be reduced as far as possible so as to reduce the pneumatic characteristic influence of the additional antenna radome on a fighter airplane. According to the aircraft wing tip antenna radome, the effective aspect ratio of a wing can be increased, so that the maximum lift coefficient of the airplane can be improved, the induction resistance can be reduced, and the pneumatic characteristic of the airplane can be improved.