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Abstract
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In the present study, a numerical simulation of turbulent flow over the NACA 65-100 compressor cascade was conducted to control the boundary layer using both suction and blowing separately. In order to study the effects of suction and blowing over the blade, 10 slots were considered on the upper surface of the blade. The slots were considered at intervals of 5% to 95% of the blade chord length. The results showed that applying both suction and blowing caused to delay the flow separation point and move it downstream which led to increase the lift coefficient and decrease the drag coefficient. Also, it was concluded that the effect of applying suction especially in the location where is near the trailing edge was significantly more than the effect of applying blowing. So that the lift coefficient had increased about 45% at 95% of chord length for suction compared to 5% of chord length and it had increased about 10% at 95% of chord length for blowing compared to 5% of chord length. Moreover, the best location to apply suction and blowing in a compressor cascade was near the flow separation point where is near the trailing edge.
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