000013981 001__ 13981
000013981 005__ 20161115094007.0
000013981 04107 $$aeng
000013981 046__ $$k2016-08-21
000013981 100__ $$aPalchekovskaya, Natalia
000013981 24500 $$aNumerical simulation of hypersonic flow over re-entry space vehicle

000013981 24630 $$n24.$$p24th International Congress of Theoretical and Applied Mechanics - Book of Papers
000013981 260__ $$bInternational Union of Theoretical and Applied Mechanics, 2016
000013981 506__ $$arestricted
000013981 520__ $$2eng$$aInt is work numerical simulation of flow over Martian space probe at wind tunnel conditions, corresponding to Mach numb rs M = 7.5, 10.5 and 14 for vari us angles of a tack (AoA) is arried out. Parallel computin is fulfilled on supercomputer using multiblock grids. Computational grids 0 various dimensions are used for verificatio of results. Comparison of b sic flow chara teristics, such as pressure coefficient and Mac number, for various flow regimes is implemented. Validation of numerical results using xperimental d ta is carried out.

000013981 540__ $$aText je chráněný podle autorského zákona č. 121/2000 Sb.
000013981 653__ $$a

000013981 7112_ $$a24th International Congress of Theoretical and Applied Mechanics$$cMontreal (CA)$$d2016-08-21 / 2016-08-26$$gICTAM2016
000013981 720__ $$aPalchekovskaya, Natalia
000013981 8560_ $$ffischerc@itam.cas.cz
000013981 8564_ $$s132812$$uhttps://invenio.itam.cas.cz/record/13981/files/PO.FM13-1.12.160.pdf$$yOriginal version of the author's contribution as presented on CD, XMLout( page 1386, code PO.FM13-1.12.160).
000013981 962__ $$r13812
000013981 980__ $$aPAPER