D,18 • CITED REFERENCES 



in the approximate solution, continuity of temperature and temperature 

 gradient at the h discontinuity is satisfied only in the mean. The solution 

 thus obtained is not valid in the immediate neighborhood of the h dis- 

 continuity (say within one thickness) but is reasonable outside such a 

 neighborhood. This is analogous to, say, the Saint Venant principle in 

 elasticity. The results are rather lengthy and cannot be given here in full 

 detail. The interested reader is referred to [30] where the detailed results 

 are given. 



D,18. Cited References. 



1. Jet Propulsion. Prepared by Staffs of Jet Propul. Lab. and Guggenheim Lab., 

 Calif. Inst. Technol. for Air Tech. Service Command, 1946. 



2. McAdams, W. H. Heat Transmission. McGraw-Hill, 1942. 



3. Boelter, L. M. K., et al. Heat Transfer Notes. Univ. Calif. Press, 1946. 



4. Jakob, M. Heat Transfer, Vol. 1. Wiley, 1949. 



5. Sutton, G. P. Rocket Propulsion Elements. Wiley, 1949. 



6. Carslaw, H. S., and Jaeger, J. C. Conduction of Heat in Solids. Oxford Univ. 

 Press, 1948. 



7. Landau, H. G. Quart. Appl. Math. 8, 8 (1950). 



8. Courant, R., and Hilbert, D. Methoden der Mathematischen Physik, Vol. 1, 2. 

 Springer, Berlin, 1931-1937. 1st English edition, Interscience, 1953. 



9. Mayer, E. Analysis of temperature transients in rocket walls. M. W. Kellogg 

 Rept. SPD 169, 1948. 



10. Geckler, R. D. Jet Propulsion 25, 31 (1955). 



11. Mayer, E. Transient thermal stresses in concentric cylindrical shells. M. W. 

 Kellogg Rept. SPD 269, 1950. 



12. Timoshenko, S. Strength of Materials, Vol. 2. Van Nostrand, 1945. 



13. Geckler, R. D. Jet Propulsion 26, 93 (1956). 



14. Mayer, E. Analysis of thermal shocks in refractories. M. W. Kellogg Rept. SPD 

 267, 1950. 



15. Westbrook, J. H., and Wulff, J. Thermal shock failure of hollow ceramic cylin- 

 ders. Mass. Inst. Technol. Meteor Rept. 43, 1949. 



16. Cheng, C. M. J. Am. Rocket Soc. 21, 147 (1951). 



17. Heisler, M. P. /. Appl. Mech. 20, 261 (1953). 



18. Mayer, E. J. Am. Rocket Soc. 22, 150 (1952). 



19. Doane, V., et al. Development of thrust chamber assemblies for ATO rocket 

 power plants. M. W. Kellogg Rept. SPD SOI, 1950. 



20. Alcoa Aluminum and its Alloys. Aluminum Corp. of America, 1947. 



21. Parke, R. M. Molybdenum as a heat resistant metal. Battelle Memorial Inst. 

 Tech. Rept. G132-1, 1950. 



22. Lowan, A. N. Duke Math. J. 1, 94 (1935). 



23. Jaeger, J. C. Phil. Mag. 7, 324 (1941). 



24. Landau, H. G., and Hicks, B. L. Transient heat flow in composite or melting 

 solids. Ballist. Research Lab. Rept. 663, 1948. 



25. Nordheim, L. W., Soodak, H., and Nordheim, G. Thermal effects of propellant 

 gases in erosion vents and guns. Natl. Defense Research Council, 1944. 



26. Evans, G. W., Isaacson, E., and McDonald, J. K. L. Quart. Appl. Math. 8, 312 

 (1950). 



27. Reinhardt, I, F., et al. Bell Aircraft Corp. Meteor Rept. BAC-26, 1950. 



28. Yachter, M. Theoretical investigation of the steady state laminar boundary 

 layer and heat transfer in supersonic nozzles. M. W. Kellogg Rept. SPD 220, 1949. 



29. Yachter, M. Effect of nozzle geometry on heat transfer in supersonic nozzles. 

 M. W. Kellogg Rept. SPD 221, 1949. 



30. Yachter, M. Two problems in heat propagation in solids. M. W. Kellogg Rept. 

 SPD 290, 1950. 



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