Recent researches of theory and experiments indicate that turbulent drag is directly related to tiny coherent(organized)structure inside the turbulent boundary

and in turbulent flow field the flow drag of the specially designed non-smooth surface can be less than that of smooth surface.Based upon the above mentioned theory

six compressor cascades with different patterned surfaces have been experimented.The profile of the cascades was chosen from a stator vane of a reference compressor.The experiments have been performed in a near-sonic wind tunnel.The results obtained at the same Mach number as the reference compressor works indicate that the appropriate patterns on the surface improve the performances of cascades.Compared with the reference smooth cascade

the best one of six tested cascades raised the critical Mach number by 7 3 percent.The air flow deflection angle at the design conditions increased by 0 9°.Correspondingly

the deviation angle decreased by 0 9°.And maximum static compression ratio rised by 0 0177.The another one of the tested cascades obtained similar results.A brief analysis of the experimental results is also presented.