Similarity Laws for Stressing Heated Wings
- Creators
- Tsien, H. S.
Abstract
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.Attached Files
Reprint - 32_Tsien_HS_1953.pdf
Files
Name | Size | Download all |
---|---|---|
md5:431a8c4bdb40c3bf215695ad2decb7ed
|
651.0 kB | Preview Download |
Additional details
- Eprint ID
- 16975
- Resolver ID
- CaltechAUTHORS:20091214-142900787
- Created
-
2009-12-14Created from EPrint's datestamp field
- Updated
-
2019-10-03Created from EPrint's last_modified field
- Caltech groups
- Guggenheim Jet Propulsion Center
- Other Numbering System Name
- Guggenheim Jet Propulsion Center
- Other Numbering System Identifier
- 32