By solving the three-dimensional Reynolds averaged Navier-Stokes (N-S) equations

the detailed flow field information of the reverser flow was obtained under different taxiing-velocity conditions during the landing process of a large transport aircraft. The single engine calculation shows that in no case the reverser flow will be re-ingested by the engine. The aircraft/engine integrated calculation indicates that with the decrease of relative wind Mach number

the possibility of the reverser flow being re-ingested by engine keeps increasing. When the relative wind Mach number decreases to 0.1

the reverser flow is re-ingested by the outboard engine. Meanwhile

the inlet flow field of the engine is distored

and the circumferential steady total pressure distortion coefficient increases obviously. When the relative wind Mach number decreases to 0.05

the reverser flow is re-ingested by both the outboard and inboard engines. When the relative wind Mach number decreases to 0

the reverser flow is not re-ingested. But the reverser flow hinders the free flow and reduces the total pressure of the free flow ingested by the engines

finally causing the inlet flow field distortion of the engine.