简介:Thispaperdevelopsahypersonicaerothermalsimulationmethodformissileslotflow.ThefinitevolumemethodofstructuregridsolverisdevelopedforsolvingEulerandNavier-Stokesequations.ThesolverincludesPark'stwotemperaturemodelandtheairmulti-speciesreactionmodel.Thesecond-orderaccuracyTVDnumericalmethodwasdeducedtocomputethehypersonicaeroheatingwhichimprovesthecomputationalefficiency.Computationalresultsaregiventoshowthehighaccuracycomparingtotheexistingexperimentaldata.