When the serpentine inlet is running at the exit Mach number Ma(subscript e)=0.45, the total pressure recovery coefficient equals 0.90, and synthesis distortion equals 13.85%.
When the serpentine inlet is running at the exit Mach number Ma(subscript e)=0.45, the total pressure recovery coefficient equals 0.90, and synthesis distortion equals 13.85%.
本研究的蛇形进气道在出口马赫数为0.45时，总压恢复系数为0.90，综合畸变指数为13.85%，总压恢复较低，畸变较大，超出了一般航空发动机的承受范围。