A forward swept rotor was produced on the basis of transonic compressor NASA rotor 11 original geometry.The steady flow fields of this forward swept rotor and rotor 11 have been numerically simulated under design rotation speed

which shows that the performance of forward swept rotor especially the stall margin has been improved.The unsteady simulation of the flow fields of forward swept rotor and rotor 11 indicates that the inlet circumferential total pressure distortion has caused the deterioration of performance.However the forward swept rotor has lower mass flow near stall point compared with the original rotor 11 under the inlet circumferential pressure distortion

because the flow field near the blade tip region benefits from the forward swept rotor.