Shock wave/boundary layer interactions induced by bump in the Bump inlet

In order to study the interactions between the conical shock wave induced by the bump of the Bump inlet and the turbulent boundary layer developed from the fuselage, and also estimate its aerodynamic advantages, the semicone and semirhombic cone of some similarities in flowfield structure with bump were selected as references. The threedimensional flowfields with these three configurations were simulated by numerical methods. Based on this, three bumps with different Mach numbers were designed and the effect of the designed Mach number on the bumps flowfield characteristic was studied. The results showed that when the inviscid shock wave strengths of three configurations were equal, the strength of the vortices induced by semicone was the strongest, followed by the bump, and that induced by the semirhombic cone was the weakest. Although the flowfield induced by the bump was very complex, the flow field behaved in quasiconical similarity manner. Although the semicone had the strongest ability to divert the boundary layer, considering the ability of diverting the boundary layer and the inlet exit distortion on the whole, bump was the best, showing why it was selected as the leading compression ramp for supersonic inlet. In addition, at the design condition, increasing the design Mach number appropriately can improve bumps ability of diverting the boundary layer. However, in case of too high designed Mach number, the ability of diverting the boundary layer could almost keep invariant, but the total pressure loss may increase rapidly.