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  • 1
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    On the quasi-conical flowfield structure of the swept shock wave-turbulent boundary layer interaction (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The swept oblique shock-wave/turbulent-boundary-layer interaction generated by a 20-deg sharp fin at Mach 4 and Reynolds number 21,000 is investigated via a series of computations using both conical and three-dimensional Reynolds-averaged Navier-Stokes equations with turbulence incorporated through the algebraic turbulent eddy viscosity model of Baldwin-Lomax. Results are compared with known experimental data, and it is concluded that the computed three-dimensional flowfield is quasi-conical (in agreement with the experimental data), the computed three-dimensional and conical surface pressure and surface flow direction are in good agreement with the experiment, and the three-dimensional and conical flows significantly underpredict the peak experimental skin friction. It is pointed out that most of the features of the conical flowfield model in the experiment are observed in the conical computation which also describes the complete conical streamline pattern not included in the model of the experiment.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-1759
    Format: text
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  • 2
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    The hypersonic shock wave-turbulent boundary layer interaction generated by a sharp fin at Mach 8.2 (1992)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: A combined experimental and numerical study has been conducted on the hypersonic shock-wave turbulent-boundary layer interaction at Mach 8.2 generated by a single fin of angles alpha = 10 and 15 deg. Three models are considered: (1) the 3D compressible Reynolds-averaged Navier-Stokes (RANS) equations using the k-epsilon turbulence model, (2) the 3D RANS using the Rodi turbulence model, and (3) the conical RANS using the Baldwin-Lomax algebraic turbulence model. The computations are compared with various experimental data. The computations using models (1) and (2) show quantitatively very similar results and very good agreement with experimental data for surface pressure and skin friction. Comparison with boundary layer profiles of pitot pressure and yaw angle are also generally good, but the peak surface heat transfer is overestimated by up to 48 percent. The effect of the laminar boundary layer on the fin is restricted to the immediate vicinity of the fin surface. Conical calculations using model (3) show substantially poorer agreement with experiment.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-0747
    Format: text
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  • 3
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    Supersonic turbulent flow past a swept compression corner at Mach 3. II (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The three-dimensional Mach 3.0 shock wave-turbulent boundary layer interaction generated by a swept compression corner whose geometry is characterized by the angle of streamwise compression angle alpha and the angle of sweep lambda is presently treated by the Baldwin-Lomax (1978) algebraic turbulent eddy viscosity model. The results obtained, and those previously derived by means of Cebeci and Smith (1974) and Jones and Launder (1972) models, are compared with experimental measurements. The rate of change of the mean kinetic energy along a streamline is investigated, and evidence is obtained that the flowfield structure is rotational and inviscid.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 88-0310
    Format: text
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  • 4
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    Three-dimensional shock wave-turbulent boundary layer interactions generated by a sharp fin at Mach 4 (1991)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: This paper describes a combined experimental and theoretical study of three-dimensional swept shock wave-turbulent boundary layer interactions at Mach 4 generated by a sharp fin of angles alpha equals 16 and 20 degrees. The theoretical model is the three-dimensional compressible Reynolds-averaged Navier-Stokes equations with turbulence incorporated through the algebraic eddy viscosity model of Baldwin and Lomax. Previous computations have been performed by Horstman using the Baldwin-Lomax, Cebeci-Smith and Jones Launder models. Computed results for the surface pressure, skin friction and streamline angles are compared with experiment and previous numerical results. The present results display good agreement with experimental data for surface pressure and surface flow direction. All turbulence models fail to accurately predict the peak skin friction. The computed flowfields are in agreement with many of the features of the quasi-conical flowfield model of Settles.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-0648
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  • 5
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    Supersonic turbulent flow past a 3-D swept compression corner at Mach 3 (1987)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Experimental and theoretical studies are presented on the three-dimensional shock wave-turbulent boundary layer interaction generated by a swept compression corner at Mach 3 for compression angle of 24 deg, sweep angle of 60 deg, and Reynolds numbers from 140,000 to 900,000. Two theoretical approaches were used, both of which utilize the full mass-averaged compressible three-dimensional Navier-Stokes equations but differ in the choice of turbulence model (the Baldwin-Lomax, 1978, and the Jones-Launder, 1972, model, respectively). The features of the computed mean flow structure were found to be qualitatively the same for both the Baldwin-Lomax and Jones-Launder models.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 87-0551
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  • 6
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    Dangers on the Ramp: Aviation Safety Reporting System (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-20
    Description: The Aviation Safety Reporting System (ASRS) in a partnership between the National Aeronautics and Space Administration (NASA), the Federal Aviation Administration (FAA), participating carriers, and labor organizations. It is designed to improve the National Airspace System by collecting and studying reports detailing unsafe conditions and events in the aviation industry. Employees are able to report safety issues or concerns with confidentiality and without fear of discipline.
    Keywords: Air Transportation and Safety
    Type: ARC-E-DAA-TN13824 , Aviation Safety InfoShare; Mar 04, 2014; Seattle, WA; United States
    Format: application/pdf
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  • 7
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    Structure of supersonic turbulent flow past a swept compression corner (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: The structure of the shock wave/turbulent boundary-layer interaction generated by a 3D swept compression corner has been investigated through a combined experimental and theoretical research program. The flowfield geometry is defined by the streamwise compression angle alpha and the sweep angle lambda of the corner. The present study examines two different configurations, namely (alpha, lambda) = (24 deg, 40 deg) and (24 deg, 60 deg) at Mach 3 and Re sigma infinity about 9 x 10 exp 5. The theoretical model is the 3D Reynolds-averaged compressible Navier-Stokes equations with turbulence incorporated using a turbulent eddy viscosity. The calculated flowfields display general agreement with experimental data for surface pressure and good agreement with experimental flowfield profiles of pitot pressure and yaw angle. The principal feature of the flowfield is a large vortical structure approximately aligned with the corner. The entrainment of incoming fluid into the vortical structure is strongly affected by the sweep angle lambda. Viscous (turbulent and molecular) effects appear to be important only in the immediate vicinity of the surface and in an isolated region within the interaction and near the corner.
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 890-896
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  • 8
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    Ground Related Safety Issues Through the Eyes of Flight Crews (2019)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: This presentation reviews voluntary safety reports received by NASA's Aviation Safety Reporting System pertaining to safety issues related to Ground Operations.
    Keywords: Air Transportation and Safety
    Type: ARC-E-DAA-TN67495 , Aviation Safety InfoShare; Apr 17, 2019; Dallas, TX; United States
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  • 9
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    Aircraft Taxi, Tow, or Pushback Gone Wrong ASRS Review of Maintenance Reports with Unintended Aircraft Movement Outcome (2018)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: This presentation reviews voluntary safety reports received by NASA's Aviation Safety Reporting System pertaining to aircraft taxi, tow, or pushback incidents during maintenance operations.
    Keywords: Air Transportation and Safety
    Type: ARC-E-DAA-TN54168
    Format: application/pdf
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  • 10
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    "ASRS Review of Terrain Critical Depressurization Procedure Planning Issues" (2018)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: This presentation reviews voluntary safety reports received by NASA's Aviation Safety Reporting System pertaining to Terrain Critical Depressurization Procedure Planning.
    Keywords: Air Transportation and Safety
    Type: ARC-E-DAA-TN54165 , Aviation Safety InfoShare; Mar 21, 2018; Baltimore, MD; United States
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