Navier-Stokes Analysis of Subsonic Flowfields over a Missile Configuration

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Subsonic e owe elds over a missile cone guration 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 e owe elds are presented intermsof particletraces,helicity contours, and surfacestreamlines. The e owseparation overthemissilebody, the development of leeward-side vortex patterns, and the canard and tail vortices and their interaction are identie ed. The computed normal force and pitching moment coefe cients compare well with the experimental data at an incidence of 15 deg. At higherincidences thenormal 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.