Measurement of distortion in second experimental control rod for argonne naval reactor with constant transverse temperature gradient and uniform longitudinal temperature distribution

Measurement of distortion in second experimental control rod for argonne naval reactor with constant transverse temperature gradient and uniform longitudinal temperature distribution

Date: September 26, 1951
Creator: Lietzke, A. F. & Nagey, T. F.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Chemical and physical properties of a boron-carbon-hydrogen fuel z-244 /naca 55z8/

Chemical and physical properties of a boron-carbon-hydrogen fuel z-244 /naca 55z8/

Date: March 27, 1956
Creator: Buddie, M.; Cramer, P. M. & Spakowski, A. E.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental Behavior of Pentaborane-Air Combustion Products During Expansion in a Convergent Divergent Nozzle

Experimental Behavior of Pentaborane-Air Combustion Products During Expansion in a Convergent Divergent Nozzle

Date: February 18, 1958
Creator: Branstetter, J. R. & Setze, P. C.
Description: In order to evaluate the post combustion behavior of boric oxide, pentaborane-air mixtures, burned to completion at a combustor pressure of 3 atmospheres, were expanded through a 7.1-inch-long convergent-divergent nozzle having a 4-inch-diameter throat and an exit-to-throat area ratio of 1.68. The experimentally determined thrust performance was in good agreement with the ideal equilibrium performance at stagnation temperatures of 3300 deg R and lower. The boric oxide vapor at the combustor exit required about 400 F deg supercooling before any condensed phase was observed. For a given thrust, fuel consumption was as much as 20 percent greater than predicted from vapor-pressure data for combustor outlet temperatures i n the vicinity of 3600 deg R. A similar result could be expected in full-scale engines, since the test combustor provided an unusually long dwell time and a highly turbulent environment. During the expansion process, the vapor (when present) did not condense to the extent predicted for an equilibrium expansion process. Moreover, condensation was observed only i n the form of small, abrupt phase changes i n the subsonic flow near the throat. Friction, due to liquid boric oxide films on the nozzle surfaces, was negligible when the surface temperature was above 800 ...
Contributing Partner: UNT Libraries Government Documents Department
Preliminary report on experimental investigation of engine dynamics and controls for a 48-inch ramjet engine

Preliminary report on experimental investigation of engine dynamics and controls for a 48-inch ramjet engine

Date: March 16, 1956
Creator: Dunbar, W. R.; Hart, C. E. & Vasu, G.
Description: Experimental investigation of engine dynamics and controls for 48-inch ramjet engine in free jet facility at Mach number 2.76 and altitudes 68,000 to 82,000 feet.
Contributing Partner: UNT Libraries Government Documents Department
Surge-inception study in a two-spool turbojet engine

Surge-inception study in a two-spool turbojet engine

Date: January 1, 1956
Creator: Lubick, R. J.; Saari, M. J. & Wallner, L. E.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of various heat exchangers for liquid-metal nuclear turbojet over range of flight and operating conditions

Comparison of various heat exchangers for liquid-metal nuclear turbojet over range of flight and operating conditions

Date: April 28, 1958
Creator: Ragsdale, R. G.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Measurement and analysis of turbulent flow containing periodic flow fluctuations

Measurement and analysis of turbulent flow containing periodic flow fluctuations

Date: August 19, 1953
Creator: Mickelsen, W. R. & Laurence, J. C.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis of rocket, ramjet, and turbojet engines for supersonic propulsion of long-range missiles.  3:  Ramjet engine performance

Analysis of rocket, ramjet, and turbojet engines for supersonic propulsion of long-range missiles. 3: Ramjet engine performance

Date: August 5, 1954
Creator: Weber, R. J. & Luidens, R. W.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Chemical and physical properties of modified Hi-Cal-2

Chemical and physical properties of modified Hi-Cal-2

Date: December 1, 1955
Creator: Allen, H., Jr.; Mcdonald, G. E. & Pusanski, B. J.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight investigation of a liquid hydrogen fuel system

Flight investigation of a liquid hydrogen fuel system

Date: August 19, 1957
Creator: Acker, L. W.; Christenson, H. H.; Gough, W. V. & Mulholland, D. R.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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