Paper presented at the 7th International Conference on Heat Transfer, Fluid Mechanics and Thermodynamics, Turkey, 19-21 July, 2010.
Numerical studies were performed to analyze effect of nozzle number of antitank guided missile(ATGM) on characteristics of a plume and supersonic jet noise and variation of thrust. The multiple nozzle has same mass flux and nozzle area ratio. When multiple nozzle of eject motor exhausts a plume outside the nozzle, the supersonic blast wave is created and makes a complicated flux. To analyze the complicated flux and to capture the shock, special techniques are required. This study adopts Roe's upwind scheme as a spatial derivative and
a second order central scheme for viscous term. The LU-SGS implicit scheme is used for time integration and for an correct prediction; this study used finite-dIifference solution of the unsteady, compressible, full Navier-Stokes equations, coupled with a two-equation k-E turbulence model. In addition, the multi-block grid technique is applied to analyze the complicated geometry of the exhaust plume.
