The physics associated with leading-edge flow reattachment and tip vortex roll-up in crossflow are incorporated into a simple theory that enables the improved prediction of the lateral static stability derivative C l β of thin low-aspect-ratio wings at low Reynolds numbers. The theory is validated against experimental stability derivative measurements of a total of 13 flat-plate wings. Accurate prediction of C l β is obtained to lift coefficients as high as 0.7. Results indicate that the tip vortex, and its expedited roll-up over thin low-aspect-ratio wings at low Reynolds numbers, is destabilizing in terms of C l β . In addition, leading-edge flow reattachment at low lift coefficients, whether in the form of a separation bubble for wings with unswept leading edges or an elongated separation region on wings with swept leading edges, may be stabilizing or destabilizing in terms of C l β based on whether the wing has forward or backward quarter-chord sweep.


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    Titel :

    Theoretical Prediction of Roll Moment Due to Sideslip for Thin Low-Aspect-Ratio Wings


    Beteiligte:
    Linehan, Thomas (Autor:in) / Mohseni, Kamran (Autor:in)

    Erschienen in:

    AIAA Journal ; 57 , 4 ; 1452-1467


    Erscheinungsdatum :

    2019-03-06


    Format / Umfang :

    16 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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