Numerical simulation of hypersonic flow over re-entry space vehicle
Abstract eng: Int 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.
Publisher:
International Union of Theoretical and Applied Mechanics, 2016
Conference Title:
Conference Title:
24th International Congress of Theoretical and Applied Mechanics
Conference Venue:
Montreal (CA)
Conference Dates:
2016-08-21 / 2016-08-26
Rights:
Text je chráněný podle autorského zákona č. 121/2000 Sb.
Record appears in:
Record created 2016-11-15, last modified 2016-11-15
guest ::
