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Showing 1 to 1 of 1 for “"Controlled Diffusion Airfoil"”.
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Experimental and Numerical Investigations of Optimized High-Turning Supercritical Compressor Blades
… 55 deg. The baseline blade was a conventional Controlled Diffusion Airfoil (CDA) design and the other two were optimized blades. The blades were tested for an inlet Mach number range from 0.61 to 0.95 and an inlet flow angle range from 44.4 deg to 50.4 deg, at high Reynolds numbers …