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As you know, the sandwich panel is widely used in aircraft structures.Commonly used as a core from honeycomb Aluminium or Nomex(Aramid).The question is in the internal structure of some Fighters such as the F-14 and F-16,... we see not uniform cell size for core of undellying wing surfaces or other control surface such as stabilizers or rudders.For example when we see distance space between leading egde and main spar the cell size(not sahpe) of honeycomb core is varying(large cell size to small) This has a reason to go back to the loading design or other factor and I want to persuade the technically or experimentally cause or causes of it .

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    $\begingroup$ Hi Ras. Please edit your original question with the added clarification so it can be reopened, instead of asking again. Also see here for help. $\endgroup$ – ymb1 Aug 25 '19 at 10:10