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    Unknown
    In:  Other Sources
    Publication Date: 2018-12-01
    Description: Turbomachinery blade designs are becoming more aggressive in order to achieve higher loading and greater range. New analysis tools are required to cope with these heavily loaded blades that may operate with a thin separated region near the trailing edge on the suction surface. An existing, viscous airfoil code was adapted to cascade conditions in an attempt to provide this capability. Comparisons with recently obtained data show that calculated and experimental surface Mach numbers were in good agreement but loss coefficients and outlet air angles were not. Previously announced in STAR as N84-24539
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-1301
    Format: text
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