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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    Title :

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


    Contributors:

    Published in:

    AIAA Journal ; 57 , 4 ; 1452-1467


    Publication date :

    2019-04-01




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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