Tsien, H. S. (1953) Similarity Laws for Stressing Heated Wings. Journal of the Aeronautical Sciences, 20 (1). pp. 1-11. http://resolver.caltech.edu/CaltechAUTHORS:20091214-142900787
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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.
|Additional Information:||Copyright, 1953, by the Institute of the Aeronautical Sciences and reprinted by permission of the copyright owner. Received June 10, 1952.|
|Group:||Guggenheim Jet Propulsion Center|
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|Usage Policy:||No commercial reproduction, distribution, display or performance rights in this work are provided.|
|Deposited By:||George Porter|
|Deposited On:||14 Dec 2009 23:01|
|Last Modified:||26 Dec 2012 11:39|
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