Aircraft wing designed for speeds in high subsonic range

摘要

The wing' aerofoil section (14) on the side of the supersonic flow area (6) has a periodical aerofoil section' variation running crossways to the airflow direction (5). This affects the thickness of the aerofoil section in the spanwise direction and in the airflow direction produces a displacement of the location of the compression shock wave (8). The period length of the aerofoil section variation crossways to the airflow direction is greater than the thickness of the boundary layer on the upper surface (3) before the compression shock wave. The displaced locations of the compression shock wave observed crossways to the airflow direction locate on a zigzag-shaped line.