The results prove that: (1) When the Mach number of the flow at the exit increases, the total pressure recovery decreases, and the circular steady total pressure distortion coefficient, turbulence intensity and synthesis distortion increase.
The results prove that: (1) When the Mach number of the flow at the exit increases, the total pressure recovery decreases, and the circular steady total pressure distortion coefficient, turbulence intensity and synthesis distortion increase.
研究结果表明：(1)地面工作状态下，随着出口马赫数的增加，蛇形进气道出口截面的总压恢复系数不断下降，而稳态周向畸变指数、紊流度和综合畸变指数均上升，稳态径向畸变指数变化不大。