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 % 本研究的蛇形進(jìn)氣道在出口馬赫數(shù)為0 . 45時(shí),總壓恢復(fù)系數(shù)為0 . 90 ,綜合畸變指數(shù)為13 . 85 % ,總壓恢復(fù)較低,畸變較大,超出了一般航空發(fā)動(dòng)機(jī)的承受范圍。