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AERONAUTICS AND SPACE aging alloy analysis angle angular application approximation assumed average calculated canopy Center characteristics coefficient component computed conductance configuration considered constant CONTINUE coordinate correlation cross section defined density determined diaphragm difference direction distance distribution driver effect element energy equation existing expansion expression face field Figure flow flux force friction function geometry given gives heat helium incident increase initial integral intensity layer measured method misalinement NASA Note nozzle obtained occurs operation pilot pilot rating plane plate predicted present pressure primary radiation range ratio reaction reference reflection region relation relative response rotational rubber scattering seal shock shock velocity shown solution station surface TECHNICAL temperature term thermal thickness tion tire trace transfer tread unit wave
Page 26 - Gaydon, AG, and Hurle, IR, The Shock Tube in High-Temperature Chemical Physics, Reinhold, New York, 1963.
Page 20 - Raters lation 1 and 2 1 and 3 1 and 4 2 and 3 2 and 4 3 and 4...
Page 47 - DC 205^6 11. Contract or Grant No. 13. Type of Report and Period Covered 2. Sponsoring Agency Name and Address 14.
Page 25 - Experimental Investigation of Attenuation of Strong Shock Waves in a Shock Tube With Hydrogen and Helium as Driver Gases.
Page 49 - RD and Morton, KW, Difference Methods for Initial -Value Problems.
Page 17 - No. 1, Feb. 1973, pp. 17-24. 4 Ludwig, Laurence P., "Face-Seal Lubrication. I — Proposed and Published Models," NASA TN D-8101, 1976. 5 Sneck, HJ, "The Effect of Geometry and Inertia on Face Seal Performance—Laminar Flow," JOURNAL OF LUBRICATION TECHNOLOGY, TRANS. ASME, Series F, Vol. 90. No.