Subsonic flowfields over a missile configuration are computed at high angles of attack ranging from 15 to 60 deg with the NASA Ames Research Center OVERFLOW Navier-Stokes solver. The computed flowfields are presented in terms of particle traces, helicity contours; and surface streamlines. The dow separation over the missile body, the development of leeward-side vortex patterns, and the canard and tail vortices and their interaction are identified. The computed normal force and pitching moment coefficients compare well with the experimental data at an incidence of 15 deg; At higher incidences the normal force is underpredicted by up to 15%. The computed pitching moments agree qualitatively well with the,experimental data, but Percentage deviations are substantial in the higher incidence range.