An attempt is made for fluidic control of the vortical flow and its related vortex breakdown phenomenon over a delta wing with a particular geometry. The model has a sweep angle of Lambda = 60 deg and a rounded leading edge. The control system is based on four rectangular slots along the portside leading edge, and it provides continuous or pulsed jets normal to the leading-edge surface and parallel to the leeward side plane. The mass flow rate and the frequency of injection can be varied independently. The results are compared to a reference case defined by a microflap fixed along the leading edge and set perpendicular to it. Qualitative measurements are obtained with surface flow visualizations and boundary-layer transition detections with acenaphten. Quantitative data consist in mean and instantaneous surface pressure distributions measurements under the primary vortex axis and in mean three-dimensional velocity held measurements. The control effect is analyzed by means or laser sheet visualizations to detect the vortex breakdown position and by normal force and rolling moment measurements with a five-component balance.


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    Title :

    Control of vortical flow over a rounded leading-edge delta wing


    Additional title:

    Beeinflussung der Wirbelströmung über einem Deltaflügel mit abgerundeter Vorderkante


    Contributors:

    Published in:

    AIAA Journal ; 43 , 7 ; 1409-1418


    Publication date :

    2005


    Size :

    10 Seiten, 22 Bilder, 34 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




    Control of Vortical Flow over a Rounded Leading-Edge Delta Wing

    Florent Renac / Didier Barberis / Pascal Molton | AIAA | 2005


    Control of vortical flows over a rounded leading-edge delta wing

    Renac, Florent / Barberis, Didier / Molton, Pascal | AIAA | 2003