000014013 001__ 14013
000014013 005__ 20161115094008.0
000014013 04107 $$aeng
000014013 046__ $$k2016-08-21
000014013 100__ $$aMohseni, Kamran
000014013 24500 $$aUnsteady Kutta condition and vortex-sheet generation

000014013 24630 $$n24.$$p24th International Congress of Theoretical and Applied Mechanics - Book of Papers
000014013 260__ $$bInternational Union of Theoretical and Applied Mechanics, 2016
000014013 506__ $$arestricted
000014013 520__ $$2eng$$aVortex method has been widely used for low-Reynolds-number flights as it reduces the computation domain from the entire flow field to only finite vortical structures. An essential challenge of the vortex method lies in the prediction of the vortex sheets separated from the solid body. To tackle this problem, this study extends the classical Kutta condition to unsteady situations based on the physical sense that flow cannot turn around a sharp edge. This unsteady Kutta condition can be readily applied to an airfoil with cusped trailing edge, where the forming vortex sheet is known to be tangential to the trailing edge. For a finite-angle trailing edge, previous studies indicate that the direction of the forming vortex sheet is ambiguous. Therefore, this study proposes a novel analytical formulation to determine the angle of the trailing-edge vortex sheet based on momentum conservation in the direction normal to the forming vortex sheet.

000014013 540__ $$aText je chráněný podle autorského zákona č. 121/2000 Sb.
000014013 653__ $$a

000014013 7112_ $$a24th International Congress of Theoretical and Applied Mechanics$$cMontreal (CA)$$d2016-08-21 / 2016-08-26$$gICTAM2016
000014013 720__ $$aMohseni, Kamran
000014013 8560_ $$ffischerc@itam.cas.cz
000014013 8564_ $$s148973$$uhttps://invenio.itam.cas.cz/record/14013/files/PO.FM15-1.12.86.pdf$$yOriginal version of the author's contribution as presented on CD, XMLout( page 1568, code PO.FM15-1.12.86).
000014013 962__ $$r13812
000014013 980__ $$aPAPER