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Aerothermodynamics of Gas Turbine and Rocket Propulsion, Volume 1
Gordon C. Oates
Limited preview - 1997
aero aerodynamic affect the mechanism airfoil anemometer angle of attack annulus apparent in shifting attempt to eval CHARACTERISTICS OF SINGLE-STAGE Compressor Flow Theory compressor performance map compressor speed compressor stage COMPRESSOR WITH HUB-TIP Copies obtainable correlation was obtained data obtained decelerating flow diagram were investigated dynamic phase angle dynamometer E53I09 tating stall effect of compressor factors that affect flow coefficients marking guide vanes hub-tip ratio hysteresis effects mechanism of rotating NACA RM E53I09 number and speed number of stall obtainable from NACA oscilloscope partial-span rotating stalls performance map reveals Prian range of weight regions during increasing RM E53I09 tating rotating-stall characteristics rotating-stall data rotating-stall pattern rotating-stall regions rotor blades rotor speed shifting the rotating-stall similar compressors SINGLE-STAGE AXIAL-FLOW COMPRESSOR single-stage compressor speed of total stall region stall was applied stall-propagation-rate parameter stalls were experimentally stator symmetrical velocity diagram THEORETICAL INVESTIGA theory on ro TION OF ROTATING-STALL Vasily Washington NACA RM weight flow