The structural response of two composite tow-steered shells without and with small cutouts in end compression is assessed using analyses and experimental measurements. The cylindrical shells are fabricated without cutouts using an automated fiber placement system. The shell layups have fiber orientation angles that vary continuously around the shell circumference, from ±10 degrees on the axially stiff crown and keel, to ±45 degrees on the shear-stiff sides. One shell with overlaps has laminate thickness buildups on the crown and keel, and the other shell without overlaps has a more uniform shell wall thickness. These shells are tested in axial compression, without and with unreinforced cutouts scaled to a commercial aircraft passenger door. Results from nonlinear finite element analyses are presented with measured loads, displacements, and strains in prebuckling, to buckling, and at stable postbuckling. Very good agreement is observed, which increases confidence for use of tow-steered composites on operational vehicles.