The effect of boundary layer blowing in the corner region of a linear compressor cascade wind tunnel
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For the corner region boundary layer blowing investigations, two slots were machined into the ends of a set of cascade blades, and an external air source was used as the blade slot jet air source. Tests were done for 19, 21, and 23 degrees angle of attack. The main effect of corner boundary layer blowing was a significant reduction in total pressure losses in the region along the blade span between the exterior portion of the corner boundary layer flow and the blade profile boundary layer flow.
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