3 pages matching displacement thicknesses in this book
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1.5 and specific 90 Nozzle exit aftermixing axial Mach aftermixing conditions aftermixing flow angle aftermixing Mach number angle and nozzle axial Mach number boundary layer characteristics characteristics of two-dimensional conditions downstream constant at values designed for free-stream displacement thicknesses Effect of nozzle effect of specific exit flow angle free-stream axial Mach free-stream Mach number further flow expansion heat ratio results higher Mach number isentropic loss-free nozzle Mach number level Mach number range Mach number solutions method of characteristics NASA TM nozzle efficiency Nozzle exit flow nozzle flow angle nozzle loss characteristics nozzle profile nozzle throat Reynolds nozzles designed nozzles with sharp-edged number of 2.5 number on nozzle oblique shock losses ratio of 1.4 result in higher sharp-edged throats shown in figure sonic aftermixing axial sonic free-stream axial sonic solution specific heat ratio subsonic aftermixing axial Supersonic aftermixing axial supersonic free-stream axial supersonic solution throat Reynolds number total-to-static pressure ratio Vanco