. . "1"^^ . . "2006-01-01+01:00"^^ . "0"^^ . "Po\u010D\u00EDta\u010Dov\u00E9 modelov\u00E1n\u00ED aeroelastick\u00FDch d\u011Bj\u016F p\u0159i obt\u00E9k\u00E1n\u00ED kmitaj\u00EDc\u00EDch profil\u016F re\u00E1lnou tekutinou zejm\u00E9na po ztr\u00E1t\u011B stability syst\u00E9mu." . "2010-06-08+02:00"^^ . "The goal is to develop numerical methods for the solution of fluid-structure interaction problems in time domain, particularly for large deformations. The main attention will be paid to the numerical simulation of unsteady, strongly nonlinear phenomena during and after starting of the aeroelastic instabilities (flutter), as well as under large forced oscillations of elastically supported airfoil excited by an external force of aerodynamical or mechanical origin. For this purpose, the computational algorithms will be worked out. They will be based on the solution of unsteady Navier-Stokes equations for incompressible fluid and large Reynolds numbers by the finite volume and stabilized finite element methods. These methods will be combined with multilevel and domain decomposition techniques. The time dependence of the computational domain will be taken into account by the ALE (arbitrary Lagrangean-Eulerian) formulation and suitable models of turbulence will be included."@en . "2009-12-31+01:00"^^ . "Byly vypracov\u00E1ny metody a v\u00FDpo\u010Detn\u00ED programy pro numerick\u00E9 simulace interakce proudu tekutiny a kmitaj\u00EDc\u00EDho t\u011Blesa v \u010Dasov\u00E9 oblasti po vzniku aeroelastick\u00E9 nestability p\u0159i velk\u00FDch v\u00FDchylk\u00E1ch a vysok\u00FDch Reynoldsov\u00FDch \u010D\u00EDslech se zahrnut\u00EDm vlivu turbulence."@cs . "Computer modelling of aeroelastic phenomena for real fluid flowing past vibrating airfoils particularly after the loss of system stability"@en . " self-oscillations" . "C\u00EDlem je rozv\u00EDjet numerick\u00E9 metody pro \u0159e\u0161en\u00ED probl\u00E9m\u016F interakce tekutiny a kmitaj\u00EDc\u00EDho t\u011Blesa v \u010Dasov\u00E9 oblasti zejm\u00E9na p\u0159i v\u011Bt\u0161\u00EDch v\u00FDchylk\u00E1ch. Hlavn\u00ED pozornost bude v\u011Bnov\u00E1na metod\u00E1m pro numerick\u00E9 simulace nestacion\u00E1rn\u00EDch, siln\u011B neline\u00E1rn\u00EDch d\u011Bj\u016F v pr\u016Fb\u011Bhu a po vzniku aeroelastick\u00FDch nestabilit (flatr) i p\u0159i velk\u00FDch vynucen\u00FDch kmitech obt\u00E9kan\u00E9ho, pru\u017En\u011B ulo\u017Een\u00E9ho profilu vybuzen\u00E9ho vn\u011Bj\u0161\u00ED silou aerodynamick\u00E9ho nebo mechanick\u00E9ho p\u016Fvodu. K tomu budou vyv\u00EDjeny a zdokonalov\u00E1ny vlastn\u00ED v\u00FDpo\u010Detn\u00ED algoritmy, kter\u00E9 budou zalo\u017Eeny na \u0159e\u0161en\u00ED proud\u011Bn\u00ED vazk\u00E9 nestla\u010Diteln\u00E9 tekutiny p\u0159i vysok\u00FDch Reynoldsov\u00FDch \u010D\u00EDslech popsan\u00E9ho nestacion\u00E1rn\u00EDmi Navierov\u00FDmi-Stokesov\u00FDmi rovnicemi. P\u016Fjde zejm\u00E9na o modelov\u00E1n\u00ED proud\u011Bn\u00ED pomoc\u00ED metody kone\u010Dn\u00FDch objem\u016F a stabilizovan\u00E9 metody kone\u010Dn\u00FDch prvk\u016F. Tyto techniky budou kombinov\u00E1ny s v\u00EDce\u00FArov\u0148ov\u00FDmi metodami, s metodou rozd\u011Blen\u00ED na podoblasti a s pou\u017Eit\u00EDm ALE (Arbitrary Lagrangian-Eulerian) formulace. Do v\u00FDpo\u010Detn\u00EDch proces\u016F budou zahrnuty n\u011Bkter\u00E9 modely turbulence." . . . . . . "Methods and computational programs for numerical simulations of interaction of fluid flows with vibrating structure in time domain during the aeroelastic instability were developed considering the large deformations, high Reynolds numbers and turbulence."@en . . . . "2009-04-28+02:00"^^ . . " finite element method" . "38"^^ . . "38"^^ . " nonlinear dynamics" . . . . . " flutter" . "aeroelastic instability" . . . "aeroelastic instability; flutter; divergence; self-oscillations; numerical simulations; nonlinear dynamics; finite element method; finite volume method"@en . " numerical simulations" . "0"^^ . . " divergence" . "http://www.isvav.cz/projectDetail.do?rowId=IAA200760613"^^ . "IAA200760613" .