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Published January 1953 | Reprint
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Similarity Laws for Stressing Heated Wings

Tsien, H. S.


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.

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August 19, 2023
October 19, 2023