<div class="description">
<dl><dd>Thesis Advisor(s): Kahn, Charles H</dd>
<dd>"December 1967."</dd>
<dd>Description based on title screen as viewed on November 19, 2007</dd>
<dd>Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, December 1967</dd>
<dd>Includes bibliographical references (p. 54-55)</dd>
<dd>The validity of conventional skin and stringer type analyses is verified experimentally for a thick milled skin aircraft structure. The accuracy of solution is evaluated by comparing the strain energies in a mathematical model to that obtained experimentally from a wing panel of a high performance aircraft. Results indicate that the conventional methods of a skin-stringer/matrix force approach are valid for a thick milled skin aircraft structure of this type provided the panel loading is neither severe nor concentrated. Additionally the grid elements chosen must be small enough to preculde any gross averaging errors</dd>
<dd>Mode of access: World Wide Web</dd>
<dd>System requirements: Adobe Acrobat Reader</dd>
<dd>US Navy (USN) author</dd>
<dd>dk/ upgraded 1/7/08</dd></dl><br>Subjects:</div>
<div class="fn value">
Parcells, Paul Whitney.</div>
Internet Archive identifier