摘要
Thispaperdevelopsahypersonicaerothermalsimulationmethodformissileslotflow.ThefinitevolumemethodofstructuregridsolverisdevelopedforsolvingEulerandNavier-Stokesequations.ThesolverincludesPark'stwotemperaturemodelandtheairmulti-speciesreactionmodel.Thesecond-orderaccuracyTVDnumericalmethodwasdeducedtocomputethehypersonicaeroheatingwhichimprovesthecomputationalefficiency.Computationalresultsaregiventoshowthehighaccuracycomparingtotheexistingexperimentaldata.
出版日期
2012年01月11日(中国期刊网平台首次上网日期,不代表论文的发表时间)