Example 11, Slide 33: STAGS model of the same simpler optimized complexly corrugated cylindrical shell with smoothing under uniform axial compression

Fig. 55 from the 2014 GENOPT paper. Top two frames: The STAGS model of the optimized specific case, narw91updown, smoothed with 9 major segments over a width of 50 inches (solid square data point in Fig. 46) plus the accumulated widths of “edge smoothing” segments.
Bottom left-hand frame: The critical general buckling mode and load factor, 1.512. Compare with the bottom right-hand frame in the previous figure.
Bottom right-hand frame: Enlarged view of the critical local buckling mode and load factor, 1.506, STAGS predicts 6 axial half-waves over the panel length, LENGTH = 100 inches, which agrees with the BIGBOSOR4 prediction. Compare with the upper left-hand frame in the previous figure.
The first 5 eigenvalues from the STAGS model shown in the top two frames are as follows:
1.506080 (local buckling, bottom right frame), 1.507613 (local buckling), 1.510155 (local buckling), 1.511830 (general buckling, bottom left frame), 1.511931 (general buckling).

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