Experimental wind tunnel tests, conducted to reproduce the base flow past a space launcher during early ascent fight conditions, were numerically simulated by solving the steady Reynolds-averaged Navier–Stokes equations using two different versions of the Spalart–Allmaras model. The launcher model consisted of a cylinder with a circular cross section, an ogival nose, and a centered nozzle that issued a supersonic cold jet embedded in the external subsonic stream. A comparative analysis of the data obtained from the steady-state simulations and from the experimental tests indicated that the launcher base pressure was closely related to the turbulent shear stresses within the jet mixing layer; therefore, accurate modeling of the compressibility effects in the turbulent mixing layer plays an important role in improving the base drag estimates provided by the numerical simulations.


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    Titel :

    Turbulence Modeling of Base Drag on Launcher in Subsonic Flight


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    2014-09-12


    Format / Umfang :

    8 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




    Venusian Probes Subsonic Drag Determination from Flight Data

    R.C. Blanchard / W.P. Phillips / G.M. Kelly et al. | AIAA | 1982



    Base-Pressure Experimental Investigation on a Space Launcher in Subsonic Regime

    Paciorri, R. / Sabetta, F. / Valenza, F. et al. | AIAA | 2013


    Subsonic induced drag

    SANDERS, K. L. | AIAA | 1965