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  • 1
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    Wall jet analysis for circulation control aerodynamics. Part 1: Fundamental CFD and turbulence modeling concepts (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: An overview of parabolic and PNS (Parabolized Navier-Stokes) methodology developed to treat highly curved sub and supersonic wall jets is presented. The fundamental data base to which these models were applied is discussed in detail. The analysis of strong curvature effects was found to require a semi-elliptic extension of the parabolic modeling to account for turbulent contributions to the normal pressure variations, as well as an extension to the turbulence models utilized, to account for the highly enhanced mixing rates observed in situations with large convex curvature. A noniterative, pressure split procedure is shown to extend parabolic models to account for such normal pressure variations in an efficient manner, requiring minimal additional run time over a standard parabolic approach. A new PNS methodology is presented to solve this problem which extends parabolic methodology via the addition of a characteristic base wave solver. Applications of this approach to analyze the interaction of wave and turbulence processes in wall jets is presented.
    Keywords: AERODYNAMICS
    Type: NASA. Ames Research Center Proceedings of the Circulation-Control Workshop, 1986; p 23-69
    Format: application/pdf
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  • 2
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    Computational models for the analysis/design of hypersonic scramjet components. I - Combustor and nozzle models (1986)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: An overview of computational models developed for the complete, design-oriented analysis of a scramjet propulsion system is provided. The modular approach taken involves the use of different PNS models to analyze the individual propulsion system components. The external compression and internal inlet flowfields are analyzed by the SCRAMP and SCRINT components discussed in Part II of this paper. The combustor is analyzed by the SCORCH code which is based upon SPLITP PNS pressure-split methodology formulated by Dash and Sinha. The nozzle is analyzed by the SCHNOZ code which is based upon SCIPVIS PNS shock-capturing methodology formulated by Dash and Wolf. The current status of these models, previous developments leading to this status, and, progress towards future hybrid and 3D versions are discussed in this paper.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 86-1595
    Format: text
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  • 3
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    Prediction of jet mean flow structure in support of HSCT noise suppression concepts (1991)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The paper describes the application of techniques based on computational fluid dynamics to the simulation of jet flowfields. A solution code for the Reynolds-averaged Navier-Stokes equations is supplemented by conventional two-equation turbulence models based on the Boussinesq approximation. The axisymmetric SCIPVIS code is enhanced with the PARCH and CRAFT codes to examine plug-jet flowfields and imperfectly expanded axisymmetric free round jets. The sensitivity of shock/boundary layer interactions is observed in simulations of the plug case, and the adaptive gridding in the disk region and turbulence levels generated at the triple point are identified as areas in the Mach case that require improvement. Jet-wave structure in the region beyond the first several shock cells can be predicted, and turbulence modeling can be undertaken with respect to improving compressibility, length scale, vorticity, and energy budget. The mean flow structure of imperfectly expanded jets can be studied to develop related noise suppression concepts for the High-Speed Civilian Transport (HSCT).
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 91-2253
    Format: text
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  • 4
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    Progress in the development of advanced computational models for the analysis of generalized supersonic jet flowfields (1990)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: This paper describes two three-dimensional computational codes (PARCH and CRAFT) for computing a generalized supersonic jet flowfields with subsonic external streams, which solve the Reynolds-averaged Navier-Stokes equations in a time asymptotic manner. The application of these codes to an imperfectly expanded jet flowfield is demonstrated. Special attention is given to numerical issues and to turbulence modeling. The application of the PARCH and CRAFT codes to other related flowfield problems, such as gas turbine and nozzle flows, and to generalized missile-plume flowfields is discussed.
    Keywords: ACOUSTICS
    Type: AIAA PAPER 90-3915
    Format: text
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  • 5
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    Implicit/explicit analysis of interactive phenomena in: supersonic, chemically-reacting, mixing and boundary layer problems (1985)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: An efficient implicit/explicit procedure for solving the parabolized Navier-Stokes (PNS) equations to analyze supersonic, viscous, chemically-reacting flows is presented. The approach combines a fully-implicit algorithm for solving the parabolic mixing/boundary layer equations with an explicit algorithm for determining the hyperbolic pressure field. The unified model, SPLITP, contains provisions for treating bounding/embedded subsonic regions using a pressure-splitting procedure which suppresses elliptic (upstream influence) effects without recourse to sublayer approximations. Several two-equation turbulence models with compressibility and curvature-correction terms are incorporated into SPLITP. Applications to a variety of flow problems are presented which include: ducted supersonic mixing and combustion flowfields, free jets and plumes, and, curved boundary layers and wall jets.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 85-1717
    Format: text
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