Supersonic S-shaped Inlet Flow Field Numerical Simulation

The three dimensional turbulent flows inside/outside the supersonic S-shaped inlet were numerically studied for various flight conditions. The flows were predicted while two fin pins was added in inlet trying to reduce flows distortion index of outlet. The calculations agree the experiments well.The following three flight conditions were simulated:①height H= 11000m, Mach number M=1.4, attack angle α = 0 , sideslip angle β = 0;②height H=11000m, Mach number M=1.4, attack angle α = 10deg, sideslip angle β=0;③height H=11000m, Mach number M=1.4, attack angle α=0, sideslip angleβ = 10 deg.The calculations of first condition were compared with test datas and that agree well.The influence of airframe/head on entrance of the inlet flow fields, the locations of shock waves and the characteristics of the flow fields inside the inlet and at the outlet of the inlet are investigated.Two pin fins were added on the back straight zoom in order to reduce distortion index of total pressure and swirls at the outlet. Flow fields in the inlet with cylinder-shaped pin fins and with similar-drop-shaped pin fins were simulated respectively. The results showed that the distortions of velocity and pressure fields in the outlet were reduced and the effect of similar-drop-shaped fins was better. But the total pressure recoveries with fin pins were less than that without fin pins.