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  • 1
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    An experimental study of shock wave/vortex interaction (1989)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The interaction of a supersonic streamwise vortices (of Mach number 2.2, 3.0, and 3.5) with a normal shock wave has been experimentally investigated, and is found to be highly unsteady. Five-hole pressure-probe and temperature measurements ahead of the interaction are used as initial conditions for an axisymmetric Navier-Stokes calculation. The numerical results supports the hypothesis that supersonic vortex breakdown is an important factor in the observed interaction flow pattern.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 89-0082
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
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    Measurements of a supersonic turbulent vortex (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Mean-flow measurements of a supersonic turbulent streamwise vortex are presented. This vortex was produced by the injection of a swirling flow along the centerline of a supersonic airstream at Mach 3. Directional Mach number distributions, obtained via a five-hole flow-angularity probe, reveal vortex characteristics similar to those of the incompressible case, even though rotational Mach numbers up to 0.8 were obtained. This work is the first step of a study of the supersonic vortex breakdown phenomenon.
    Keywords: AERODYNAMICS
    Type: Symposium on Turbulence; Oct 17, 1988 - Oct 19, 1988; Rolla, MO; United States
    Format: text
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    NASA TECHNICAL REPORTS
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