A zonal, implicit, time-marching Navier-Stokes computational technique has been used to compute three dimensional, multiple jet interaction flow fields for a projectile containing rocket motors in the ogive section. Numerical flow field computations have been made for both transverse and angled nose jets/rockets at supersonic speeds using Chimera overset grids. How computations for the angled jet case includes modeling the inside of the nose rocket. The jet conditions include very high jet to free stream pressure ratio and high temperature. Computed results show the qualitative features of the cpmplex jet interaction flow field including the flow field downstream of the jet. The computed results are used to obtain the aerodynamic forces and moments including the thrust of the rocket. The jet interference drag has been compared with the experimental data and is found to be in good agreement. The computed thrust was compared with the experimental data and was found to be in the right range Since the jets function only for 3 sec in a 40 sec flight trajectory, jet-off condition has also been computed to determine the effective drag penalty for that flight condition.
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