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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
open access

Localization of Cerium-144 in the Skeletal Tissues of Fetal Rats

Description: The developing fetal skeleton of the rat was used to study the microscopic localization of the rare earth Ce/sup 144/ in bone. Nineteen-day-old rat fetuses were injected with Ce/sup 144/ in isotonic sodium citrate via the umbilical vein. They were sacrificed one-haif hour after the injection by immersion in 80% alcohol fixative. The fetuses were embedded in paraffin and sectioned at 10 to 12 mu . Semiserial sections were treated with periodic acid- Schiff stain for mucopolysaccharides, and by t… more
Date: October 18, 1957
Creator: Asling, C. W.; Johnston, M. E.; Durbin, P. W. & Hamilton, J. G.
Partner: UNT Libraries Government Documents Department
open access

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
open access

Some Effects of Heat Transfer at Mach Number 2.0 at Stagnation Temperatures Between 2,310 and 3,500 Degrees R on a Magnesium Fin With Several Leading-Edge Modifications

Description: Report presenting testing of four models of a thin magnesium fin, with the leading edge swept back 35 degrees, of a type used to stabilize the first stages of rocket-propelled multistage hypersonic models. The investigation was carried out to determine some effects of aerodynamic heating at high stagnation temperatures on the leading edges of fins and to determine the relative effectiveness of several leading-edge protective methods. The fins tested included a basic fin, a fin with a blunt lead… more
Date: April 18, 1957
Creator: Bland, William M., Jr. & Bressette, Walter E.
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
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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

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

Analysis of Limitations Imposed on One-Spool Ducted-Fan-Engine Designs by Compressors and Turbines at Flight Mach Numbers of 0, 0.6, and 0.8

Description: Memorandum presenting an analysis of one-spool ducted-fan engines in order to determine the primarily limitations on ducted-fan-engine design and to compare this type with the turboprop and turbojet engines for the same application. Designs were studied at flight Mach numbers of 0 and 0.6 at sea level and Mach numbers of 0.6 and 0.8 at the tropopause. Results regarding the discussion of charts, effect of design parameters on turbine stress, effect of design parameters, effect of design paramete… more
Date: July 18, 1957
Creator: Cavicchi, Richard H.
Partner: UNT Libraries Government Documents Department
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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

Continuous dissolution of uranium fuel elements in a tower dissolver

Description: A continuous process for the dissolution of irradiated fuel elements is a potential means of solving criticality limitations in the dissolution of enriched uranium slugs and of achieving higher dissolver capacity in the Redox and Purex Plants. This report summarizes development studies aimed at determination of dissolution rates, effluent compositions, and effects of changes in operating conditions on mercury-catalyzed dissolution in a tower-type unit.
Date: June 18, 1957
Creator: Evans, T. F.
Partner: UNT Libraries Government Documents Department
open access

Investigation of a nonlinear control system

Description: A discontinuous variation of coefficients of the differential equation describing the linear control system before nonlinear elements are added is studied in detail. The nonlinear feedback is applied to a second-order system. Simulation techniques are used to study performance of the nonlinear control system and to compare it with the linear system for a wide variety of inputs. A detailed quantitative study of the influence of relay delays and of a transport delay is presented.
Date: October 18, 1957
Creator: Flügge-Lotz, I.; Taylor, C. F. & Lindberg, H. E.
Partner: UNT Libraries Government Documents Department
open access

Trip to Selas Corporation of America

Description: On May 23, 1957, a visit was made by the writer to the Selas Corporation of American in Dresher, Pennsylvania. The purpose of the visit was to discuss further investigations into methods of tubesheet brazing by direct heating. Original work along these lines has been carried out at ORNL and is covered by a memo (CF-57-4-57) to W.D. Manly, dated April 16, 1957, and entitled : Investigation of Tubesheet Brazing by a Method of Direct Heating.
Date: June 18, 1957
Creator: Franco-Ferreira, E. A.
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
open access

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

PRELIMINARY RADIATION SURVEY OF THE SRE

Description: An investigation was conducted to determine radiation dosags rates associated with operation of the Sodium Reactor Experiment at 8.3 Mw. These values were extrapolated to full-power operation. Hadiation survey results are tabulated. (J.R.D.)
Date: September 18, 1957
Creator: Hale, J.P.
Partner: UNT Libraries Government Documents Department
open access

Effect of Core Corrosion Sample Assembly on HRT Critical Concentration

Description: An estimate has been made of the critical fuel concentration in the HRT, taking into account the effect of the core corrosion sample assembly. The estimate is based on a number of previous calculations of critical concentration in an un-poisoned reactor and one calculation of critical concentration as a function of poison level. The makeup of the first core corrosion sample assembly was used in calculating equivalent neutron poisoning effects. Figure 1 shows the estimated critical concentration… more
Date: July 18, 1957
Creator: Haubenreich, Paul N.
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
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
open access

A Method of Computing the Transient Temperature of Thick Walls From Arbitrary Variation of Adiabatic-Wall Temperature and Heat-Transfer Coefficient

Description: "A method of calculating the temperature of thick walls has been developed in which the time series and the response to a unit triangle variation of surface temperature concepts are used, together with essentially standard formulas for transient temperature and heat flow into thick walls. The method can be used without knowledge of the mathematical tools of its development. The method is particularly suitable for determining the wall temperature in one-dimensional thermal problems in aeronautic… more
Date: June 18, 1957
Creator: Hill, P. R.
Partner: UNT Libraries Government Documents Department
open access

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
open access

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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