To enable adjustment of bleeding flow amount based on pressure variation in an air intake structure for a supersonic airplane.

Plural bores 2 are provided on a wall surface 1 of an air intake bleeding boundary layer and flexible rubber rings 3 are attached in the bores 2. When pressure at a bleeding bore part is low and required bleeding amount is small, a bleeding opening part 3a of the rings 3 are not expanded so widely and a diameter is small as d1 (a), (b). When pressure is high and required bleeding amount is large, the bleeding opening part 3b of the rings 3 is expanded and a diameter becomes d2 (d2>d1). The opening part changes based on pressure variation at the bleeding opening part and bleeding amount become adjustable.