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  • 1
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    Kinetic theory of axially elastic spherocylinder molecules (1974)
    American Institute of Physics
    Details
    Publication Date: 1974-08-15
    Print ISSN: 0021-9606
    Electronic ISSN: 1089-7690
    Topics: Chemistry and Pharmacology , Physics
    Published by American Institute of Physics
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    PAPER CURRENT
  • 2
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    Structure of a shock wave in a vibrationally relaxing diatomic gas (1975)
    American Institute of Physics
    Details
    Publication Date: 1975-01-01
    Print ISSN: 0031-9171
    Topics: Physics
    Published by American Institute of Physics
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    PAPER CURRENT
  • 3
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    An approach to the calculation of the pressure field produced by rigid wide chord dual rotation propellers of high solidity in compressible flow (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An unsteady lifting service theory for the counter-rotating propeller is presented using the linearized governing equations for the acceleration potential and representing the blades by a surface distribution of pulsating acoustic dipoles distributed according to a modified Birnbaum series. The Birnbaum series coefficients are determined by satisfying the surface tangency boundary conditions on the front and rear propeller blades. Expressions for the combined acoustic resonance modes of the front prop, the rear prop and the combination are also given.
    Keywords: ACOUSTICS
    Type: AIAA PAPER 86-0467
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Incompressible lifting-surface aerodynamics for a rotor-stator combination (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Current literature on the three dimensional flow through compressor cascades deals with a row of rotor blades in isolation. Since the distance between the rotor and stator is usually 10 to 20 percent of the blade chord, the aerodynamic interference between them has to be considered for a proper evaluation of the aerothermodynamic performance of the stage. A unified approach to the aerodynamics of the incompressible flow through a stage is presented that uses the lifting surface theory for a compressor cascade of arbitrary camber and thickness distribution. The effects of rotor stator interference are represented as a linear function of the rotor and stator flows separately. The loading distribution on the rotor and stator flows separately. The loading distribution on the rotor and stator blades and the interference factor are determined concurrently through a matrix iteration process.
    Keywords: AERODYNAMICS
    Type: NASA-TM-83767 , E-2258 , NAS 1.15:83767
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Acoustic pressures emanating from a turbomachine stage (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A knowledge of the acoustic energy emission of each blade row of a turbomachine is useful for estimating the overall noise level of the machine and for determining its discrete frequency noise content. Because of the close spacing between the rotor and stator of a compressor stage, the strong aerodynamic interactions between them have to be included in obtaining the resultant flow field. This paper outlines a three-dimensional theory for determining the discrete frequency noise content of an axial compressor consisting of a rotor and a stator each with a finite number of blades. The lifting surface theory and the linearized equation of an ideal, nonsteady compressible fluid motion are used for thin blades of arbitrary cross section. The combined pressure field at a point of the fluid is constructed by linear addition of the rotor and stator solutions together with an interference factor obtained by matching them for net zero vorticity behind the stage.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-2325
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Acoustic pressures emanating from a turbomachine stage (1984)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A knowledge of the acoustic energy emission of each blade row of a turbomachine is useful for estimating the overall noise level of the machine and for determining its discrete frequency noise content. Because of the close spacing between the rotor and stator of a compressor stage, the strong aerodynamic interactions between them have to be included in obtaining the resultant flow field. A three dimensional theory for determining the discrete frequency noise content of an axial compressor consisting of a rotor and a stator each with a finite number of blades are outlined. The lifting surface theory and the linearized equation of an ideal, nonsteady compressible fluid motion are used for thin blades of arbitrary cross section. The combined pressure field at a point of the fluid is constructed by linear addition of the rotor and stator solutions together with an interference factor obtained by matching them for net zero vorticity behind the stage.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-83734 , E-2217 , NAS 1.15:83734 , Aeroacoustics Meeting; Oct 15, 1984 - Oct 17, 1984; Williamsburg, VA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    An analysis for the sound field produced by rigid wide cord dual rotation propellers of high solidarity in compressible flow (1986)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An unsteady lifting service theory for the counter-rotating propeller is presented using the linearized governing equations for the acceleration potential and representing the blades by a surface distribution of pulsating acoustic dipoles distributed according to a modified Birnbaum series. The Birnbaum series coefficients are determined by satisfying the surface tangency boundary conditions on the front and rear propeller blades. Expressions for the combined acoustic resonance modes of the front prop, the rear prop and the combination are also given.
    Keywords: AERODYNAMICS
    Type: NASA-TM-87178 , E-2826 , NAS 1.15:87178 , Aerospace Sciences Meeting; Jan 06, 1986 - Jan 08, 1986; Reno, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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