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Project TitleACD Aerodynamic design of Multistage Axial-Flow Compressors
Track CodeLEW-17448
DescriptionACD is a streamline analysis code for the aerodynamic design of multistage axial-flow compressors. The aerodynamic solution gives velocity diagrams on the streamlines at the blade-row edges. Blade elements are defined by a centerline curve and a thickness distribution. The blade-element inlet and outlet angles are established through empirical incidence and deviation angle adjustments to the velocity diagrams. Blade-element pressure-loss coefficients are specific either by tabular input or internal correlation. The blade elements can be stacked to give the full blade design.
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ACD - Contains Execute, Samples Request Key

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