Abstract: The near wake flow and pressure distribution on the rear end of a 25°slant angle Ahmed model were investigated at the Reynolds number of 8.7×105 ,using Cobra probe,pres-sure scanner and oil film flow visualization technique.Deflectors with different width mounted on the top edge and both side edges of the slant were tested to compare their effects on the near wake and aerodynamic drag.It is found that there is a pair of symmetrical tailing vortices in the near wake,which induces strong downwash flow near wake centerline.The strength of tailing vortices is inherently correlated with the pressure distribution on rear end and aerodynamic drag of the model.A stronger trailing vortex corresponds to larger negative pressure on the slant and also a larger aerodynamic drag.The deflectors at both sides of slant with the width of 1% model length result in about 3 .0% increase of the aerodynamic drag.With the width increases to 2% and 3%of model length,deflectors at both sides of slant can noticeably suppress the separation bubble, and result in a drag reduction of 3 .5%and 7 .2%,respectively.Deflector at the top edge prevents flow reattachment on the slant,thus eliminates the separation bubble.It suppresses the tail vor-tices and reduces the aerodynamic drag more effectively than those at the side edges.The drag re-duction rate reaches 9 .3%,1 0 .7% and 1 0 .9% for the top edge deflectors with the width of 1%, 2% and 3% of model length.