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 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 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 . 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 based on whether the wing has forward or backward quarter-chord sweep.
Theoretical Prediction of Roll Moment Due to Sideslip for Thin Low-Aspect-Ratio Wings
AIAA Journal ; 57 , 4 ; 1452-1467
2019-03-06
16 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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