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The coupled convective and radiation heat transfer of a liquid launch vehicle is studied by employing a method which combines the experimental tests and the numerical simulations. The multiphase Navier-Stokes equations, radiative transfer equations and realizable k-e turbulence model are used to establish the rocket plumes flow model with free stream at high altitude. By using the discrete-ordinates methods and the second order TVD upwind scheme in the spatial discretization, the heat flux in different typical altitude is calculated. The accuracy and effectivness of this established model is verified by presenting the comparative experimental data and the resulta show that the radiation heatflux of the altitude. The convection heat flux of the afterbody increases firstly and then decreases, the peak of the convection heat flux the thermal protection system of the liquid launch vehicle. [ABSTRACT FROM AUTHOR]