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․ Dae Seok Bae***ABSTRACT A computational analysis of nozzle flow characteristics and p lume structure is conducted to examine performance of the supersonic nozzle employed in a thruster for ground firing test. At first, flow simulations in two-dimensional converging-diverging nozzle are performed for the verification of computational capability as well as turbulence model validity. Axisymmetric converging-diverging nozzles for ground firing test are analyzed with the k-ω SST model. A performance penalty caused by flow separation in a diverging section is observed in initially -designed nozzle. The performance could be enhanced by the modification of the diverging section of nozzle contour.            . 2   ,         . k-ω SST   Reynolds-averaged Navier-Stokes  2     ,         .        . Key Words: Hydrazine Thruster( ), Ground Firing Test(), Performance Analysis(), Converging Diverging Nozzle( )

Performance Analysis and Configuration Design of the Thruster Nozzle for Ground-firing Test and Evaluation