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Creep of 2S-O Aluminum Sheet at 500 and 550 C

Description: Abstract: "Creep and creep-rupture tests were made on 25-O aluminum sheet at temperatures of 500 and 550 C. The estimated stresses that will produce 0.5 per cent deformation and rupture in 10,000 hours at 400, 450, 500, and 550 C (data at 400 and 450 C are from BMI-T-29, dated June 9, 1950) are presented."
Date: September 11, 1952
Creator: VanEcho, J. A.; Simmons, W. F. & Cross, H. C.
Partner: UNT Libraries Government Documents Department
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Mammalian Radiation Genetics

Description: "This symposium is concerned with the basic aspects of radiation effects. When we turn to the genetic effects of radiation in mammals, there are so few aspects on which there is any information that the problem of sorting out the fundamental findings has hardly arisen. In this paper it will, therefore, be possible to survey most of what is known and pass on to a consideration of what is needed next. Since one of the purposes of this symposium is an interchange of views between investigators in … more
Date: August 11, 1952
Creator: Russell, W. L.
Partner: UNT Libraries Government Documents Department
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Solution of Experimental Breeder Reactor Slugs

Description: From abstract: "A full-scale, always-safe, metal dissolver for Experimental Breeder Reactor fuel was designed, built, and installed for test operation. It was found that the dissolver operated satisfactorily, and feasible operating procedures were established for the dissolution of bare, or jacketed, EBR slugs. Minor modifications of the dissolver design have been required to accomodate [sic] a modified EBR slug, but it is believed that this will not significantly affect its operating character… more
Date: March 11, 1952
Creator: Sampson, E. M., Jr.
Partner: UNT Libraries Government Documents Department
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Metallurgical Evaluation of the Uranium Rods Rolled for the Chalk River Pile Test

Description: Summary: "The laboratory data collected during the metallurgical evaluation of these rods indicate that lower rolling temperatures increased the ultimate and yield strength, the amount of cold work, and the degree of preferred orientation existing in these uranium rods."
Date: September 11, 1952
Creator: Sanderson, M. J. & Hueschen, R. E.
Partner: UNT Libraries Government Documents Department
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Criticality Conditions for 1.75 Per Cent Enriched Uranium Slugs

Description: Abstract: "A batch of slugs is being prepared for which the U-235 content will be 1.75 per cent, and it is of interest to calculate the minimum number of such slugs required for a critical assembly in water. Using Handbook (CL-697) methods, a critical assembly of these slugs arranged in a lattice with a spacing of 5.5 cm."
Date: September 11, 1952
Creator: Erkman, John O.
Partner: UNT Libraries Government Documents Department
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Use of the Boiler Neutron Source for Exponential Experiments

Description: The following report deals with the application of the water boiler neutron source to the exponential experiments in an attempt to speed up lattice testing measurements.
Date: December 11, 1952
Creator: Davenport, D. E.
Partner: UNT Libraries Government Documents Department
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The Distribution of Uranium-Vanadium Deposits in the Colorado Plateau Relative to Tertiary Intrusive Masses

Description: Introduction: Studies of uranium-vanadium occurrences in the Four Corners region show that, with the exception of the Lukachuai area, all of the major deposits in the Morrison formation are grouped around the various igneous masses which are scattered irregularly throughout the Colorado Plateau. The pattern of deposition varies from mountain group to mountain group and each will be described separately. Maps accompany this report to supplement the descriptions of ore occurrences in the vicinity… more
Date: June 11, 1952
Creator: Reinhardt, Elmer V.
Partner: UNT Libraries Government Documents Department
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Process Engineering Report. Operating Manual For Supervisory Personnel For Green Salt Plant Of The Feed Materials Production Center, Fernald, Ohio. Part IX, Section No. 5-3. (Job No. 3004)

Description: A manual for supervisory personnel to aid in formulating detailed instructions for operators and foremen employed in a green salt plant is given. A description of the processsteps in plant operation is contained. (C.J.G.)
Date: December 11, 1952
Creator: Innes, E. D.; Holby, G. V. & Snyder, W.
Partner: UNT Libraries Government Documents Department
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Investigation at Mach Number 1.91 of Spreading Characteristics of Jet Expanding From Choked Nozzles

Description: Report presenting an investigation at Mach number 1.91 to determine the gross spreading characteristics of jets expanding from convergent and convergent-divergent nozzles using total-temperature surveys. Results regarding the preliminary development and jet spreading characteristics of the different types of nozzles are provided.
Date: February 11, 1952
Creator: Rousso, Morris D. & Baughman, L. Eugene
Partner: UNT Libraries Government Documents Department
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Experimental investigation of a two-dimensional split-wing ram-jet inlet at Mach number of 3.85

Description: Performance characteristics of a two-dimensional isentropic diffuser have been experimentally determined at a Mach number of 3.85. At zero angle of attack, a maximum total-pressure recovery of 0.41 was obtained with a supercritical mass-flow ratio of 0.95. As a consequence of the twin-duct arrangement of the diffuser, a large discontinuity in pressure recovery and mass flow with a characteristic hysteresis was encountered between critical and subcritical operation. An asymmetric shock pattern w… more
Date: August 11, 1952
Creator: Connors, James F. & Woollett, Richard R.
Partner: UNT Libraries Government Documents Department
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Longitudinal Stability and Drag Characteristics at Mach Numbers From 0.75 to 1.5 of an Airplane Configuration Having a 60 Degree Swept Wing of Aspect Ratio 2.24 as Obtained From Rocket-Propelled Models

Description: Report discussing testing of a rocket-propelled airplane configuration model and a drag model, each with a 60 degree swept wing of aspect ratio 2.24, and different fuselages, at a Mach number range of 0.75 to 1.50. Information about the longitudinal stability, control, and drag characteristics and minimum-drag characteristics is presented.
Date: April 11, 1952
Creator: Vitale, A. James; McFall, John C., Jr. & Morrow, John D.
Partner: UNT Libraries Government Documents Department
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Transonic Flight Tests to Determine Zero-Lift Drag and Pressure Recovery of Nacelles Located at the Wing Tips on a 45 Degree Sweptback Wing and Body Combination

Description: Report presenting the zero-lift drag of a sweptback wing and body combination with nacelles with NACA 1-50-250 nose inlets locate in the wing tips as determined by flight tests of rocket-powered models at transonic speeds. Results regarding the pressure recovery and the effect of the nacelles on it are also provided.
Date: January 11, 1952
Creator: Hoffman, Sherwood & Pepper, William B., Jr.
Partner: UNT Libraries Government Documents Department
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Investigation at a Mach Number of 1.2 of Two 45 Degree Sweptback Wings Utilizing NACA 2-006 and NACA 65A006 Airfoil Sections

Description: Report presenting an investigation in the low-turbulence pressure tunnel at Mach number 1.2 to determine lift, drag, and moment characteristics of a wing with an airfoil section designed for maximum lift at low speeds, 45 degrees of sweepback, aspect ratio 4, and taper ratio 0.6. A similar wing with the NACA 65A006 airfoil section was also investigated and compared to the experimental wing.
Date: September 11, 1952
Creator: Wilson, Homer B., Jr.
Partner: UNT Libraries Government Documents Department
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Analysis of Fully Developed Turbulent Heat Transfer at Low Peclet Numbers in Smooth Tubes With Application to Liquid Metals

Description: From Introduction: "Analyses of heat transfer for liquid metals flowing turbulently in smooth tubes (low Pradtl numbers) are given in reference 1 and 2. The predicted heat-transfer coefficients from these analyses are considerably higher than those determined in the experimental heat-transfer investigations for mercury and lead bismuth given in references 2 to 4. If the analytical and experimental results for flow of gases are compared at low Peclet numbers, they are also found to be in disagre… more
Date: August 11, 1952
Creator: Deissler, Robert G.
Partner: UNT Libraries Government Documents Department
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Force characteristics in the submerged and planing condition of a 1/5.78-scale model of a hydro-ski-wheel combination for the Grumman JRF-5 airplane

Description: From Summary: "Force characteristics determined from tank tests of a 1/5.78-scale model of a hydro-ski-wheel combination for the Grumman JRF-5 airplane are presented. The model was tested in both the submerged and planing conditions over a range of trim, speed, and load sufficiently large to represent the most probable full-size conditions."
Date: July 11, 1952
Creator: Land, Norman S. & Pelz, Charles A.
Partner: UNT Libraries Government Documents Department
open access

Tests at Mach Number 1.62 of a Series of Missile Configurations Having Tandem Cruciform Lifting Surfaces

Description: Memorandum presenting an investigation at a Mach number of 1.62 in the 9-inch supersonic tunnel of a series of missile configurations with tandem lifting surfaces of low aspect ratio and of nearly equal span. Some of the variables investigated were interdigitation angle, wing and tail plan form, and longitudinal location of wing with respect to tail. Lift, drag, and pitching-moment data are presented, together with center-of-pressure locations and tail-lift efficiency factors.
Date: January 11, 1952
Creator: Grigsby, Carl E.
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Low-Speed Longitudinal Stability Characteristics of a Swept-Wing Airplane Model With Two Modifications to the Wing-Root Plan Form

Description: Report presenting a wind-tunnel investigation to determine the effects of two wing-root leading-edge plan-form modifications, including a notched leading-edge fillet and a rounded leading-edge fillet, on the low-speed longitudinal stability characteristics of an airplane model with a 50.7 degree sweptback wing. Results regarding stability at zero lift, variation of stability with lift coefficient, and lift and drag characteristics are provided.
Date: July 11, 1952
Creator: Kemp, William B., Jr.
Partner: UNT Libraries Government Documents Department
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Low-speed longitudinal aerodynamic characteristics of a twisted and cambered wing of 45 degree sweepback and aspect ratio 8 with and without high-lift and stall-control devices and a fuselage at Reynolds numbers from 1.5 x 10(exp 6) to 4.8 x 10(exp 6

Description: Report presenting a low-speed investigation of the static longitudinal aerodynamic characteristics of a twisted and cambered wing with 45 degrees of sweepback and an aspect ratio of 8.0 in the 19-foot pressure tunnel. Testing included the effects of leading- and trailing-edge flaps, flow control fences, and a fuselage. Report presenting longitudinal stability characteristics, lift characteristics, drag characteristics, fuselage effects, Reynolds number effects, effect of wing roughness are prov… more
Date: June 11, 1952
Creator: Salmi, Reino J.
Partner: UNT Libraries Government Documents Department
open access

Control characteristics at transonic speeds of a linked flap and spoiler on a tapered 45 degrees sweptback wing of aspect ratio 3

Description: Report presenting an investigation at transonic speeds to determine the control characteristics of a linked flap and spoiler. The control consisted of a linked combination of a quarter-span inboard plug-type spoiler and a full-span flap. Results regarding the hinge-moment, pitching-moment, lift, and rolling-moment are provided.
Date: July 11, 1952
Creator: Lockwood, Vernard E. & Fikes, Joseph E.
Partner: UNT Libraries Government Documents Department
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The aerodynamic characteristics of a supersonic aircraft configuration with a 40 degree sweptback wing through a Mach number range from 0 to 2.4 obtained from various sources

Description: "A summary and analysis have been made of the results of various investigations to determine the aerodynamic characteristics of a supersonic aircraft configuration. The configuration has a wing with 40 degree sweepback at the quarter-chord line, aspect ratio 4, taper ratio 0.5, and 10-percent-thick circular-arc sections normal to the quarter-chord line. Experimental data were available for a Mach number range from 0.16 to 2.32. Results obtained from wing-flow, rocket-model, transonic-bump, and … more
Date: April 11, 1952
Creator: Spearman, M. Leroy & Robinson, Ross B.
Partner: UNT Libraries Government Documents Department
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Longitudinal Frequency-Response Characteristics of the Douglas D-558-I Airplane as Determined From Experimental Transient-Response Histories to Mach Number of 0.90

Description: Report presenting information regarding transient oscillations observed in response to elevator pulses of the Douglas D-558-I airplane at a range of Mach numbers and altitudes. An application of the Fourier transform was used to obtain the frequency-response characteristics. The effects of lift coefficient on the frequency response are also included.
Date: February 11, 1952
Creator: Angle, Ellwyn E. & Holleman, Euclid C.
Partner: UNT Libraries Government Documents Department
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Investigation at Mach number 1.91 of spreading characteristics of jet expanding from choked nozzles

Description: It is demonstrated that the temperature profiles of jets expanding into a supersonic stream are considerably smaller than the temperature profiles of jets expanding into quiescent air. The effect on the wake of varying afterbody geometry is shown to be small. The gross spreading characteristics of jets expanding from convergent and convergent-divergent nozzles in the base of a body of revolution with various boattail configurations at a Mach number of 1.91 are presented.
Date: January 11, 1952
Creator: Rousso, Morris D. & Baughman, L. Eugene
Partner: UNT Libraries Government Documents Department
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