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2.0 Lower-surface Mach 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 boundary layer characteristics boundary layer parameters boundary layer separation designed for inlet displacement thickness Effect of lower-surface 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 oblique shock losses Prandtl-Meyer angle increases 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 surface Prandtl-Meyer angles Upper-surface Mach number upper-surface Prandtl-Meyer angle