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Combustor performance of a 16-inch ram jet using gaseous hydrogen as fuel at Mach number 3.0

Description: An investigation was conducted in the NACA Lewis 10- by 10-foot supersonic wind tunnel to evaluate the performance of three burner configurations in a 16-inch ram jet with gaseous hydrogen as fuel. Data were obtained over a fuel-air-ratio range from 0.0030 to 0.0260 (stoichiometric = 0.0292) at a free-stream Mach number of 3.0 and 0 degree angle of attack. The exit nozzle-throat area ratios employed were 0.60 and 0.75.
Date: January 18, 1957
Creator: Wasserbauer, Joseph F. & Wilcox, Fred A.
Partner: UNT Libraries Government Documents Department
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Component performance investigation of J71 experimental turbine 8: effect of first-stator adjustment; internal flow conditions of J71-97 turbine with 70-percent-design stator area

Description: Results of a survey investigation of the J71-97 experimental three-stage turbine equipped with a first-stator area 70 percent pf design are presented and compared with the turbine with a first-stator area 97 percent of design.
Date: January 18, 1957
Creator: Petrash, Donald A.; Schum, Harold J. & Davison, Elmer H.
Partner: UNT Libraries Government Documents Department
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Effect of burner design variables on performance of 16-inch diameter ram-jet combustor using gaseous-hydrogen fuel

Description: An evaluation of the effect of geometric design variables on the performance of a 16-inch-diameter ram-jet combustor total pressures from 7 to 44 inches of mercury absolute. Equivalent ratio was varied from 0.1 to 1.0 at a combustor inlet temperature of 1100 degrees R.
Date: January 18, 1957
Creator: Krull, H. George & Burley, Richard R.
Partner: UNT Libraries Government Documents Department
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An Evaluation of the Calder Hall Type of Nuclear Power Plant

Description: Abstract: Presented herein is the preliminary design of a natural uranium, graphite moderated, CO2-cooled reactor and power plant similar to, but larger than, the British Calder Hall plant, with a net electrical output of 130 MWE.
Date: January 18, 1957
Creator: Banks, William F.; Schneider, G. A.; Morgan, William T. & Ash, E. B.
Partner: UNT Libraries Government Documents Department
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Experimental investigation of flow fields at zero sideslip near swept- and unswept-wing-fuselage combinations at low speed

Description: Report presenting an experimental determination of the flow fields near swept- and unswept-wing-fuselage combinations at zero sideslip as determined experimentally at low speed for various spanwise and vertical locations and angles of attack as variations with chordwise distance. Results regarding the swept-wing-fuselage flow fields, unswept-wing-fuselage flow fields, and a comparison of wing-fuselage and fuselage-alone flow fields are provided.
Date: January 18, 1957
Creator: Alford, William J., Jr. & King, Thomas J., Jr.
Partner: UNT Libraries Government Documents Department
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Internal performance of several auxiliary air inlets immersed in a turbulent boundary layer at Mach numbers of 1.3, 1.5, and 2.0

Description: Internal performance of normal-shock rectangular, circular, and scoop inlets and of external-compression inlets experimentally obtained with varying immersion in a turbulent boundary layer. Recoveries varied from about 95 percent of theoretical in the free stream to 80 percent with complete immersion, while the corresponding mass flows were usually above 95 percent of theoretical. Turning of the flow through 10 degrees caused losses in pressure recovery of 0.03 to 0.07. External compression did… more
Date: January 18, 1957
Creator: Huff, Ronald G. & Anderson, Arthur R.
Partner: UNT Libraries Government Documents Department
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Investigation of Drag and Static Longitudinal and Lateral Stability Characteristics of a Model of a 40.4 Degree Swept-Wing Airplane at Mach Numbers of 1.56 and 2.06

Description: Memorandum presenting an investigation to determine the drag, longitudinal stability, and lateral stability characteristics of a model of a fighter-type airplane. Several modifications were made to the model in an attempt to eliminate pitch-up.
Date: January 18, 1957
Creator: Carmel, Melvin M. & Turner, Kenneth L.
Partner: UNT Libraries Government Documents Department
open access

Origin and Prevention of Crash Fires in Turbojet Aircraft

Description: "The tendency for the jet engine rotor to continue to rotate after crash presents the probability that crash-spilled combustibles suspended in the air or puddled on the ground at the engine inlet may be sucked into the engine. Studies with jet engines operating on a test stand and full-scale crashes of turbojet-powered airplanes showed that combustibles drawn into the engine in this way ignite explosively within the engine. Experiment showed that the gas flow through the engine is too rapid to … more
Date: January 18, 1957
Creator: Pinkel, I. Irving; Weiss, Solomon; Preston, G. Merritt & Pesman, Gerard J.
Partner: UNT Libraries Government Documents Department
open access

RMF MEASUREMENTS ON MTR-IRRADIATED EUROPIUM OXIDE

Description: Aluminum capsules with Al inserts and He atmospheres and containing 4 strips of Eu/sub 2/O/sub 3/-stainless steel were measured in the Reactivity Measurement Facility at MTR, both before and after irradiation. (T.R.H.)
Date: January 18, 1957
Creator: Henscheid, J.W. & Fast, E.
Partner: UNT Libraries Government Documents Department
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Use of Sandia Corporation Analog Computer in Sled Design

Description: This report presents a formula developed to calculate, by means of an analog computer, the forces acting on a rocket sled.
Date: January 18, 1957
Creator: Maloney, F. J.
Partner: UNT Libraries Government Documents Department
open access

Concentration of Radioisotopes in Columbia River Whitefish in the vicinity of the Hanford Atomic Products Operation

Description: Results of a study on the uptake of radioisotopes by Columbia River whitefish for the period of June 1950 to December 1956 are presented. Differences in concentrations of radioactive materials as related to geographical location, season, age, specific tissue, and concentration of reactor effluent in the river are discussed. Changes in concentration with cooking were determined.
Date: February 18, 1957
Creator: Watson, D. G. & Davis, J. J.
Partner: UNT Libraries Government Documents Department
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A phenomenological relation between stress, strain rate, and temperature for metals at elevated temperatures

Description: Report presenting a phenomenological relation between stress, strain rate, and temperature to account for the behavior of polycrystalline metals above the equicohesive temperature. This is because the behavior of metals at elevated temperatures is constantly becoming a more important problem. The validity of the relation suggested in the equation appears to be accurate for 7075-T6 aluminum alloy.
Date: February 18, 1957
Creator: Stowell, Elbridge Z.
Partner: UNT Libraries Government Documents Department
open access

Pressure, flow, and temperature responses to a rapid plugging of a process tube

Description: This report presents the results of initial experiments concerning the protection afforded by the Panellit system against hazards associated with the inadvertent plugging of a process tube.
Date: February 18, 1957
Creator: Hesson, G. M. & Thorne, W. L.
Partner: UNT Libraries Government Documents Department
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Pyrochemical Separations Processes of Potential HAPO Interest

Description: A survey of the literature of pyrochemical processing has been made with the intent to present the theory, status, and application to future HAPO technology.
Date: February 18, 1957
Creator: Moore, R. H.
Partner: UNT Libraries Government Documents Department
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Reference Design for an OMR-Powered 38,000-DWT Tanker

Description: Abstract: This report presents a reference design of an organic moderated and cooled reactor for the propulsion of a 38,000-dwt tanker.
Date: March 18, 1957
Creator: Gimera, R. J. & Stanbridge, R. E.
Partner: UNT Libraries Government Documents Department
open access

TBP Stripping in Bubble-Cap Column and Con-Comitant Product Evaporation

Description: A study was conducted to demonstrate the stripping and evaporation steps in a Purex-type uranium recovery prccess and to ascertain the operating behavior of the equipment under a range of conditions. The factors considered were control, effectiveness, and reliability of equipment and optimum feed pcint. Experimental procedures are described, and recominendations for equipment mcdifications are included. (J.R.D.)
Date: March 18, 1957
Creator: Long, J. T.
Partner: UNT Libraries Government Documents Department
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TBP Stripping in Bubble-Cap Column and Concomitant Product Evaporation

Description: A study was conducted to demonstrate the stripping and evaporation steps in a Purex-type uranium recovery process and to ascertain the operating behavior of the equipment under a range of conditions. The factors considered were control, effectiveness, and reliability of equipment and optimum feed point. Experimental procedures are described, and recommendations for equipment modifications are included. (J.R.D.)
Date: March 18, 1957
Creator: Long, J. T.
Partner: UNT Libraries Government Documents Department
open access

Boundary-Layer-Transition and Heat-Transfer Measurements from Flight Tests of Blunt and Sharp 50 Degree Cones at Mach Numbers from 1.7 to 4.7

Description: Boundary-layer-transition and heat-transfer measurements were obtained from flight tests of blunt and sharp cones having apex angles of 50 deg. The test Mach number range was from 1.7 to 4.7, corresponding to free-stream Reynolds numbers, based on cone base diameter, of 18. 3 x 10(exp 6) and 32.1 x 10(exp 6), respectively. Transition on both models occurred at a local Reynolds number of 1 x 10(exp 6) to 2 X 10(exp 6) based on distance from the stagnation point. Transition Reynolds numbers base… more
Date: April 18, 1957
Creator: Chauvin, Leo T. & Speegle, Katherine C.
Partner: UNT Libraries Government Documents Department
open access

Heat Transfer and Boundary-Layer Transition on a Highly Polished Hemisphere-Cone in Free Flight at Mach Numbers Up to 3.14 and Reynolds Numbers Up to 24 X 10(Exp 6)

Description: "A highly polished hemisphere-cone having a ratio of nose radius to base radius of 0.74 and a half-angle of 14.5 degrees was flight tested at Mach numbers up to 4.70. Temperature and pressure data were obtained at Mach numbers up to 3.14 and a free-stream Reynolds number of 24 x 10(exp 6) based on body diameter. The nose of the model had a surface roughness of 2 to 5 microinches as measured with an interferometer" (p. 1).
Date: April 18, 1957
Creator: Buglia, James J.
Partner: UNT Libraries Government Documents Department
open access

Heat-Transfer and Pressure Distribution on Six Blunt Noses at a Mach Number of 2

Description: Report presenting testing on six blunt-nose models at angles of attack ranging from 0 to 5 degrees in order to evaluate the heat transfer and pressure on their surfaces. Information about transition, proper design, and locations of greatest and least heat transfer is provided.
Date: April 18, 1957
Creator: Carter, Howard S. & Bressette, Walter E.
Partner: UNT Libraries Government Documents Department
open access

Measurements of Heat Transfer and Boundary-Layer Transition on an 8-Inch-Diameter Hemisphere-Cylinder in Free Flight for a Mach Number Range of 2.00 to 3.88

Description: "Measurements of aerodynamic heat transfer have been made along the hemisphere and cylinder of a hemisphere-cylinder rocket-propelled model in free flight up to a Mach number of 3.88. The test Reynolds number based on free-stream condition and diameter of model covered a range from 2.69 x l0(exp 6) to 11.70 x 10(exp 6). Laminar, transitional, and turbulent heat-transfer coefficients were obtained" (p. 1).
Date: April 18, 1957
Creator: Garland, Benjamine J. & Chauvin, Leo T.
Partner: UNT Libraries Government Documents Department
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