COMPUTATION OF HYPERSONIC HIGH-TEMPERATURE NOZZLE-FLOW

A Finite-Element-procedure for the solution of the Euler equations uti lizing unstructured grids with adaptive remeshing has been employed fo r the numerical simulation of thrust nozzle flowfields. The numerical scheme and the high temperature gas models required for the completion of the equation system are described. The gas models applied are ther mally perfect gas, frozen in the combustion chamber, or a Bray-model b ased on a reaction kinetics calculation of the freezing line. Flowfiel d results and global performance values are presented in the case of a two-dimensional SERN nozzle for three operating points along an ascen t trajectory and the deviations of the global values due to the gas mo del chosen are discussed.