## Report, Volume 955U.S. Government Printing Office, 1950 - Aeronautics |

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absolute coefficient ahead air angles Ames Aeronautical Laboratory Angle of attack appendix approximate solution axial length axial velocity AXIAL-FLOW COMPRESSOR axially symmetric flow blade force blade height blade region blade-row aspect ratio continuity equation continuity relation density distribution of specific dr dr entropy equa equal equation 14g equation Dl4 gas particle gas properties given gives incompressible flow infinite aspect ratio inlet Langley Aeronautical Laboratory limiting Mach Lincoln Wolfenstein machine magnitude mass of gas mean radius motion of gas nontapered passage obtained from equation passage walls percent radial displacement radial motion radial variation radial-flow path rotor blade shown in figure simplified-radial-equilibrium calculation specific mass flow stator steady axially symmetric stream surface successive blade rows symmetrical velocity diagram tangential component tangential velocity tapered passage tion total enthalpy type of design typical stage unit mass variation of axial variation of gas velocity of gas zero aspect zero-aspect-ratio