Separated flows behind afterbodies in the high subsonic regime are investigated experimentally. Measurements or mean and unsteady wall pressure have been performed in a transonic wind tunnel on axisymmetric configurations with a propulsive jet. It is found that the distance between the base plane and the nozzle exit section, namely, the rear-body extension, is a determining parameter. For a long enough rear-body extension, the separated flow reattaches at the end of the external nozzle wall. The spectra in the reattachment region exhibit a weakly defined maximum, which is associated with the shear layer vortices impinging the downstream surface. For a short rearbody extension, the reattachment on the downstream nozzle wall is not possible. The spectra in the whole region exhibit a well-defined periodicity that corresponds to the formation of large-scale structures in the wake, as observed for bluff bodies. This is confirmed by a two-point correlation analysis of the turbulent signals, which shows that the flow is dominated by a highly coherent antisymmetric mode at the vortex shedding frequency.


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    Title :

    Analysis of unsteadiness in afterbody transonic flows


    Additional title:

    Analyse Druckschwankungen im Heckbereich transsonisch umströmter Rotationskörper


    Contributors:
    Depres, D. (author) / Reijasse, P. (author) / Dussauge, J.P. (author)

    Published in:

    AIAA Journal ; 42 , 12 ; 2541-2550


    Publication date :

    2004


    Size :

    10 Seiten, 19 Bilder, 1 Tabelle, 21 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




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