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A New Anionic Solvent Extraction Technique

Description: From abstract: "The extraction of acids with long-chain amines is described. Preliminary results on the extraction of the amine salts of polonium, plutonium and uranium are given."
Date: July 17, 1952
Creator: Moore, F. L.; Kelley, M. T. & Susano, C. D.
Partner: UNT Libraries Government Documents Department
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Analysis of Bulk Shielding Facility Neutron Dosimeter Data

Description: Technical report calculating "effective removal cross sections" for Pb, Fe and O from measurements of fast neutron does in the water surrounding the BSF reactor. The values for Pb and Fe agree quite well with those previously determined from Lid tank data, whereas that for O is somewhat lower. [From Abstract]
Date: July 17, 1952
Creator: Podgor, S.
Partner: UNT Libraries Government Documents Department
open access

Design basis for proposed separations facility, for use in preliminary project proposal

Description: Members of the Working Committees for RDA DC-4 and RDA DC-7 (KE and KW Reactors) have reviewed and approved the design basis being used for the preparation of the 200 Area portion of the Program X preliminary project proposal. This design basis includes the following: plant capacity of 275 tons per month, average flow rate; the basic chemical process used will be the Purex process; the plant will be located in the Southeast Quadrant of the 200 East Area; the plant will contain a double line of … more
Date: March 17, 1952
Partner: UNT Libraries Government Documents Department
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Effects of High Intensity Radiant Energy on Skin: [Part] 1. Type of Energy and Its Relation to Energy Delivery Rate

Description: Abstract: Burn lesions were produced by radiant energy, 3100 A to 22000 A, on depilated rat skin. The gross and microscopic pathological changes so caused are described and correlated with the amounts of incident energy and the rate of energy delivery. Within the limits studied, 0.2 to 64 cal./cm.2/sec. and 0.1 to 8.0 seconds, it was found that increasing the rate of energy delivery lowered the amount of energy required to produce a specified degree of tissue injury. The tissue changes were in … more
Date: March 17, 1952
Creator: Sheline, Glenn E.; Alpen, Edward L.; Kuhl, P. R. & Ahokas, A.
Partner: UNT Libraries Government Documents Department
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Decay Tables for the Natural Radioactive Series III. Thorium (4n) Series

Description: The third in this series of reports presents tables dealing with the growth and decay of members of the thorium family of naturally occurring radioisotopes. The general equations and approximations used in computing these tables are the same as those presented in Part I of the series.
Date: November 17, 1952
Creator: Kirby, H. W.
Partner: UNT Libraries Government Documents Department
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THERMAL CONDUCTIVITY DATA FOR SOME NUCLEAR FUELS

Description: Thermal conductivity data are reported for some mixtures of UO/sub 2/ with MgO, BeO, and Zr; U with Zr and Mg; several amaples of B/sub 4/C; and two ceramic insulators. (auth)
Date: October 17, 1952
Creator: McCreight, L.R.
Partner: UNT Libraries Government Documents Department
open access

The dynamic-response characteristics of a 35 degree swept-wing airplane as determined from flight measurements

Description: From Summary: "The longitudinal and lateral-directional dynamic-response characteristics of a 35 degree swept-wing fighter-type airplane determined from flight measurements are presented and compared with predictions based on theoretical studies and wind-tunnel data. Flights were made at an altitude of 35,000 feet covering the Mach number range of 0.50 to 1.04. A limited amount of lateral-directional data were also obtained at 10,000 feet. The flight consisted essentially of recording transient… more
Date: September 17, 1952
Creator: Triplett, William C.; Brown, Stuart C. & Smith, G. Allan
Partner: UNT Libraries Government Documents Department
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Method for Estimating Pitching-Moment Interference of Wing-Body Combinations at Supersonic Speed

Description: Report presenting an investigation into the effects of interference at supersonic speeds on the aerodynamic properties of wing-body combinations to determine the pitching moments. The correlation points of various wing-body shapes are provided and suggestions for modifications are made.
Date: April 17, 1952
Creator: Kaattari, George E.; Nielsen, Jack Norman & Pitts, William C.
Partner: UNT Libraries Government Documents Department
open access

Analysis of a Nuclear-Powered Liquid-Metal Ducted-Fan Cycle

Description: From Introduction: "The results are presented for flight Mach numbers of 0.9 to 1.5 at an altitude of 50,000 feet. The effect of flight altitude on optimum engine design-point airplane performance is also shown."
Date: December 17, 1952
Creator: Rom, F. E. & Wachtl, W. W.
Partner: UNT Libraries Government Documents Department
open access

Theoretical Investigation of the Stability at Negative Static Margins of a Supersonic Missile With an Autopilot Sensitive to Pitch Angle and Pitching Velocity

Description: Memorandum presenting stability charts covering a range of small positive and negative static margins for a supersonic missile with an autopilot sensitive to angle of pitch and rate of pitch. The results in the form of stability boundaries and lines of constant damping ratio and period show that time lags have an adverse effect on stability, but this can be counteracted by using ample gain in the rate-of-pitch feedback loop. Methods of simplifying the characteristic stability equation are discu… more
Date: March 17, 1952
Creator: Cole, Henry A., Jr. & Abramovitz, Marvin
Partner: UNT Libraries Government Documents Department
open access

Analysis of a Nuclear-Powered Liquid-Metal Ducted-Fan Cycle

Description: From Introduction: "The results are presented for flight Mach numbers of 0.9 to 1.5 at an altitude of 50,000 feet. The effect of flight altitude on optimum engine design-point airplane performance is also shown."
Date: December 17, 1952
Creator: Rom, F. E. & Wachtl, W. W.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Turbines for Driving Supersonic Compressors: 1: Design and Performance of First Configuration

Description: Report presenting the design and performance of a turbine to drive a supersonic compressor in order to determine the problems that would be encountered in turbines required to drive high-speed, high-weight-flow compressors. A model of the turbine was built and operated over a range of speed and total-pressure ratios. Results regarding performance, the effects of rotor choking, and possible modifications to the design are provided.
Date: June 17, 1952
Creator: Stewart, Warner L.; Schum, Harold J. & Whitney, Warren J.
Partner: UNT Libraries Government Documents Department
open access

Effects of wing elasticity on the aerodynamic characteristics of a 45 degree sweptback-wing-fuselage combination measured in the Langley 8-foot transonic tunnel

Description: Report presenting testing of a wing-fuselage configuration with a wing of 45 degrees sweepback of the 0.25-chord line, aspect ratio of 4, taper ratio of 0.6, and NACA 65A006 airfoil sections in aluminum and steel at a range of Mach numbers and angles of attack to determine effects of wing elasticity. Results regarding the relative effects of bending and torsion, wing-tip twist, aerodynamic characteristics, and some theoretical considerations are provided.
Date: September 17, 1952
Creator: Osborne, Robert S. & Mugler, John P., Jr.
Partner: UNT Libraries Government Documents Department
open access

Investigation at high and low subsonic Mach numbers of two symmetrical 6-percent-thick airfoil sections designed to have high maximum lift coefficients at low speeds

Description: Report presenting an investigation at high and low subsonic Mach numbers of two symmetrical 6-percent-thick airfoil sections derived to have high maximum lift at low speeds. The high-speed portion of the investigation included lift, drag, and pitching moment measurements.
Date: October 17, 1952
Creator: Paradiso, Nicholas J.
Partner: UNT Libraries Government Documents Department
open access

Investigation of ram-jet afterburning as a means of varying effective exhaust nozzle area

Description: Report presenting a discussion of the flow mechanism in an afterburner extension to a ramjet engine. An experimental evaluation of the operation of 16-inch ramjet equipped with an afterburner at Mach number 1.8 and 2.0 in the supersonic wind tunnel. The experimental data confirmed the proposed method of afterburner operation.
Date: November 17, 1952
Creator: Perchonok, Eugene & Wilcox, Fred A.
Partner: UNT Libraries Government Documents Department
open access

An Experimental Investigation of the Base Pressure Characteristics of Nonlifting Bodies of Revolution at Mach Numbers From 2.73 to 4.98

Description: Report presenting an investigation in the supersonic wind tunnel to determine some of the base pressure characteristics of related bodies of revolution at zero angle of attack. The basic body shape was a 10-caliber tangent ogive nose with a cylindrical afterbody, while other shapes tested had either a blunt-nosed profile or a boat-tailed afterbody. Results regarding the variation of pressure over the base, variation of base pressure with Reynolds number, effect of nose and afterbody shape, vari… more
Date: September 17, 1952
Creator: Reller, John O., Jr. & Hamaker, Frank M.
Partner: UNT Libraries Government Documents Department
open access

Observations of Unsteady Flow Phenomena for an Inclined Body Fitted with Stabilizing Fins

Description: Memorandum presenting an investigation of the variations with Mach number and angle of attack of the dynamic rolling-moment characteristics of a slender body of revolution in combination with a cruciform tail in the 6- by 6-foot supersonic wind tunnel. Oscillograph records of the instantaneous rolling moment of the model were obtained for Mach numbers of 0.90, 1.20, 1.40, 1.53, 1.60, and 1.70 at a constant free-stream Reynolds number. Results regarding dynamic rolling moments and visual flow st… more
Date: January 17, 1952
Creator: Mead, Merrill H.
Partner: UNT Libraries Government Documents Department
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Investigation of internal film cooling of exhaust nozzle of a 1000-pound-thrust liquid-ammonia liquid-oxygen rocket

Description: Report presenting an investigation of internal film cooling of the exhaust nozzle of a 1000-pound-thrust liquid ammonia liquid-oxygen rocket engine. With water as a coolant, approximately 16 percent of the total propellant and coolant flow was required to film-cool the entire nozzle and with anhydrous liquid ammonia, approximately 19 percent of the total flow was required. Results regarding the coolant results and performance results are provided.
Date: June 17, 1952
Creator: Abramson, Andrew E.
Partner: UNT Libraries Government Documents Department
open access

Comparison of Locked-Rotor and Windmilling Drag Characteristics of an Axial-Flow-Compressor Type Turbojet Engine

Description: The internal drag of an axial-flow turbojet engine with the rotor locked in place to prevent windmilling and with the engine windmilling was obtained over a range of simulated Mach numbers. The corrected internal drag of the engine with the locked rotor was 210 pounds or only 46 percent of the windmilling drag at a flight Mach number of 0.8.
Date: January 17, 1952
Creator: Vincent, K. R.; Huntley, S. C. & Wilsted, H. D.
Partner: UNT Libraries Government Documents Department
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