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  • 1
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    Quantitative density visualization in a transonic compressor rotor (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The flow in a 59-cm-diameter high-work transonic compressor rotor has been visualized using a fluorescent gas, 2,3, butanedione, as a tracer. The technique allows the three-dimensional flow to be imaged as a set of distinct planes. Quantitative static density maps were obtained by correcting the images for distortion and nonlinearities introduced by the illumination and imaging systems. These images and maps were used to analyze the three-dimensional nature of the blade's boundary layer and shock system.
    Keywords: AERODYNAMICS
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    A comparison of the computed and experimental three dimensional flow in a transonic compressor rotor (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The three dimensional inviscid flow in a transonic compressor rotor; total pressure ratio of 1.65, has been numerically computed using MacCormack's time-marching method. This solution is compared to intra-blade static density measurements obtained by gas fluorescence. These results and comparisons illustrate the importance of three dimensional flow phenomena in determining the rotor flow field and show that while the viscous phenomena have an important influence, particularly on the outflow, the inviscid computation properly models the flow in the inlet portion of the rotor passages.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 76-368 , Fluid and Plasma Dynamics Conference; Jul 14, 1976 - Jul 16, 1976; San Diego, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Quantitative density visualization in a transonic rotor (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The flow in a two foot diameter transonic rotor has been visualized using a fluorescent gas, 2, 3 butanedione, as a tracer. The technique allows the three dimensional flow to be imaged as a set of distinct planes. Quantitative static density maps can be obtained after correcting the images for distortion and nonlinearities introduced by the illumination and imaging systems. The visualized flow is compared to data taken simultaneously by high frequency pressure transducers near the rotor entrance and exit planes.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 75-24 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 20, 1975 - Jan 22, 1975; Pasadena, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Shock structure in transonic compressor rotors (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The inadequacy of axisymmetric theory in modeling the structure of the shock system in a transonic compressor rotor is shown with a simple model. A more accurate model for the flow near the sonic radius is proposed, which is supported by some flow visualization data and three-dimensional computations.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 17; Apr. 197
    Format: text
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    NASA TECHNICAL REPORTS
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