Advanced computational models which solve the full (FNS) and parabolized (PNS) Navier-Stokes equations for the analysis of missile aerodynamic problems with exhaust plume interactions are described. The models utilize conservative implicit algorithms and include finite-rate chemistry, two-equation turbulence models, and preliminary multi-phase flow capabilities. In the tactical missile arena, a 3D Navier-Stokes code, PARCH, was developed to analyze missile/plume interactions with both conventional nozzle exhausts, as well as with bifurcated/scarfed nozzle exhausts. The PNS work has focused on supersonic/hypersonic applications utilizing time-iterative upwind numerics for enhanced robustness and accuracy, and has included the analysis of aerodynamic, plume, and propulsive problems for missiles as well as for reentry and aerospace vehicles.


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    Title :

    Computational Models with Advanced Thermochemistry for the Analysis of Missile/Plume Flowfield Interactions


    Contributors:
    S. M. Dash (author) / N. Sinha (author) / B. J. York (author)

    Publication date :

    1990


    Size :

    30 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English






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    Recent advances in jet/plume flowfield simulation

    Dash, S / Sinha, N / Kenzakowski, D et al. | AIAA | 1995