Analytical Investigation of Blade Efficiency for Two-dimensional Supersonic Turbine Rotor Blade SectionsNational Aeronautics and Space Administration, 1970 - 20 pages |
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28 Lower-surface Prandtl-Meyer adverse pressure gradients aftermixing axial Mach Aftermixing flow angle aftermixing Mach number angle and inlet angle on rotor angle or Mach axial Mach number blade passage blade solidity boundary layer characteristics boundary layer parameters boundary layer separation decreases designed for inlet displacement thickness Effect of upper-surface effects of inlet efficiencies were obtained efficiency and boundary efficiency for two-dimensional flow had mixed flow separation free-stream axial Mach ideal passage incompressible form factor inlet flow angle inlet Mach number inlet spacing isentropic loss model Lower-surface Mach number Lower-surface Prandtl-Meyer angle Mach number levels maximum value method of characteristics number of 2.5 number on blade outlet flow angle produce vortex flow rotor blade efficiency rotor blade sections rotor blades designed shown in figures sonic sonic solution static-pressure ratio supersonic aftermixing axial supersonic rotor blade supersonic solution surface Mach number surface Prandtl-Meyer angles Upper-surface Mach number upper-surface Prandtl-Meyer angle