cranfield0013

<DOC>
<DOCNO>
13
</DOCNO>
<TITLE>
similarity laws for stressing heated wings .
</TITLE>
<AUTHOR>
tsien,h.s.
</AUTHOR>
<BIBLIO>
j. ae. scs. 20, 1953, 1.
</BIBLIO>
<TEXT>
  it will be shown that the differential equations for a heated
plate with large temperature gradient and for a similar plate at
constant temperature can be made the same by a proper modification
of the thickness and the loading for the isothermal plate .
this fact leads to the result that the stresses in the heated plate
can be calculated from measured strains on the unheated plate by
a series of relations, called the /similarity laws ./  the application
of this analog theory to solid wings under aerodynamic heating
is discussed in detail .  the loading on the unheated analog
wing is, however, complicated and involves the novel concept
of feedback and /body force/ loading .  the problem of stressing
a heated box-wing structure can be solved by the same analog
method and is briefly discussed .
</TEXT>
</DOC>