A controlled circulation trailing edge design method for compressor blade was proposed to increase the circulation and the turning angle of cascades through the specific geometrical modelling at the region of 2% chord length of trailing edge. The conclusion was verified under different Mach numbers and Reynolds numbers. The numerical results showed that

for the cascade with the diffusion factor up to 0.52 at design condition

the controlled circulation trailing edge can improve the flow turning angle by about 21% while the total pressure loss was nearly kept unchanged. Some controlled circulation trailing edge designs can even have positive effect on the decrease of loss. At the same flow turning angle

the cascade with the controlled circulation trailing edge can have lower total pressure loss than that with traditional rounded trailing edge.