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Beneficiation of Monument Number 2 Ore Apache County, Arizona

Description: From introduction: The Monument No. 2 mine is in the Navajo Indian Reservation, Apache County, Arizona, about 20 miles southwest from the San Juan River at Mexican Hat, Utah, and 26 miles southwest from Mexican Water, Arizona. The property has been operated, since its discovery, by Vanadium Corporation of America, which holds a 10-year mining lease, granted through the Interior Department, to 43 acres of ground. History of the discovery of the deposit is vague, but reportedly it was first seen … more
Date: February 27, 1952
Creator: Sheridan, M. J.
Partner: UNT Libraries Government Documents Department
open access

An Elementary Treatment of Gamma-Ray Heating and Gamma-Ray Dosage in Inhomogeneous Reactors

Description: An analysis is made of the heat produced by the absorption of gamma rays in a sample placed into a reactor. It is clearly shown that enormous local (space) variations in gamma flux exist in current reactors. An application to the Hanford reactors is treated in some detail. Although the estimates obtained may be good to but a factor of two, it is clearly shown that in most cases the major portion of the heating is due to (n, {gamma}) reactions within the sample itself, and in some cases to the g… more
Date: October 27, 1952
Creator: Primak, W.
Partner: UNT Libraries Government Documents Department
open access

A High Vacuum High Speed Ion Pump

Description: A vacuum pump based on the properties of a magnetically collimated electric discharge is described. It has a speed in the range 3000 to 7000 liters a second and a base pressure in the order of 10{sup-6}mm.
Date: August 27, 1952
Creator: Foster, J. S., Jr.; Lawrence, E. O. & Lofgren, E. J.
Partner: UNT Libraries Government Documents Department
open access

Experimental Investigation of Average Heat-Transfer and Friction Coefficients for Air Flowing in Circular Tubes Having Square-Thread-Type Roughness

Description: "An investigation of forced-convection heat transfer and associated pressure drops was conducted with air flowing through electrically heated Inconel tubes having various degrees of square-thread-type roughness, an inside diameter of 1/2 inch, and a length of 24 inches were obtained for tubes having conventional roughness ratios (height of thread/radius of tube) of 0 (smooth tube), 0.016, 0.025, and 0.037 over ranges of bulk Reynolds numbers up to 350,000, average inside-tube-wall temperatures … more
Date: June 27, 1952
Creator: Sams, Eldon W.
Partner: UNT Libraries Government Documents Department
open access

Analysis of a liquid-metal turbine-propeller cycle for propulsion of low-speed nuclear- powered aircraft

Description: From Introduction: "The intermediate subsonic speed range is considered and the liquid-metal turbine-propeller cycle discussed in this report. In this report, compressor pressure ratio, heat-exchanger air-inlet Mach number, and turbine-inlet temperature were optimized for maximum engine net thrust per engine-plus-heat exchanger weight (minimum airplane gross weight) for a range of heat-exchanger effective wall temperature."
Date: May 27, 1952
Creator: Rom, F. E. & Wachtl, W. W.
Partner: UNT Libraries Government Documents Department
open access

Investigation at low speed of the downwash, sidewash, and wake characteristics behind a large-scale triangular wing, including the effects of yaw, full-span trailing-edge flaps, and two leading-edge modifications

Description: Report presenting an investigation at low speed in the Langley full-scale tunnel of the downwash, sidewash, and wake behind a large-scale 60 degree triangular wing with 10-percent-thick biconvex airfoil sections. Results regarding the air-stream surveys for three different configurations and stability and trim are provided.
Date: October 27, 1952
Creator: Whittle, Edward F., Jr. & Hawes, John G.
Partner: UNT Libraries Government Documents Department
open access

Experimental Investigation of Axial-Flow Compressor Stator Blades Designed to Obtain High Turning Angles by Means of Boundary-Layer Suction

Description: Memorandum presenting an investigation to determine the practicability of using blade boundary-layer control in order to obtain high turning angles in a stator-blade row. The overall performance of the stage was obtained for a range of weight flows at each of three tip speeds with and without hub section. Results regarding slot configuration, overall performance, and stator-blade wakes are provided.
Date: June 27, 1952
Creator: Costello, G. R.; Cummings, R. L. & Serovy, G. K.
Partner: UNT Libraries Government Documents Department
open access

The Effects of Camber and Leading-Edge-Flap Deflection on the Pressure Pulsations on Thin Rigid Airfoils at Transonic Speeds

Description: Report discussing an investigation into the effects of camber and leading-edge-flap deflection on the pressure pulsations on thin rigid airfoils at a range of Mach numbers. The ideal camber or flap deflection was found to be dependent on Mach number and normal-force coefficient. The results of this testing, which used a 64A006 airfoil, was compared to previous testing using a 65A006 airfoil.
Date: October 27, 1952
Creator: Humphreys, Milton D. & Kent, John D.
Partner: UNT Libraries Government Documents Department
open access

Effects of the spanwise, chordwise and vertical location of an external store on the aerodynamic characteristics of a 60 degree delta wing at Mach numbers of 1.41, 1.62, and 1.96

Description: Report presenting an investigation in the supersonic blowdown tunnel to determine the effects of external store location on the lift, drag, and pitching-moment characteristics of a 60 degree delta wing at Mach numbers of 1.41, 1.62, and 1.96. Brief comparative tests were also made to determine the effect of changing the sweep of the strut attaching the store to the wing and of changing the chordwise location of the swept strut.
Date: October 27, 1952
Creator: Jacobsen, Carl R.
Partner: UNT Libraries Government Documents Department
open access

Analysis of a liquid-metal turbine-propeller cycle for propulsion of low-speed nuclear-powered aircraft

Description: From Introduction: "The intermediate subsonic speed range is considered and the liquid-metal turbine-propeller cycle discussed in this report. In this report, compressor pressure ratio, heat-exchanger air-inlet Mach number, and turbine-inlet temperature were optimized for maximum engine net thrust per engine-plus-heat-exchanger weight (minimum airplane gross weight) for a range of heat-exchanger effective wall temperature."
Date: May 27, 1952
Creator: Wachtl, William W. & Rom, Frank E.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of the Low-Speed Static and Rotary Stability Derivatives of a 0.13-Scale Model of the Douglas D-558-II Airplane in the Landing Configuration

Description: Report presenting a wind-tunnel investigation to determine the low-speed static and rotary stability derivatives of a model of the Douglas D-558-II airplane in the landing configuration. Results regarding the static longitudinal characteristics, static lateral characteristics, characteristics in rolling flow, and characteristics in yawing flow are provided.
Date: August 27, 1952
Creator: Queijo, M. J. & Wells, Evalyn G.
Partner: UNT Libraries Government Documents Department
open access

Analysis of Stage Matching and Off-Design Performance of Multistage Axial-Flow Compressors

Description: From Introduction: "The present report is intended to give a qualitative picture of the operation of each stage of a multistage compressor over a range of actual operating conditions from 50 to 100 percent design speed and to point out some means of achieving improved off-design performance. The method used in the report is primarily analytical and is based on single-stage-performance results."
Date: June 27, 1952
Creator: Finger, Harold B. & Dugan, James F., Jr.
Partner: UNT Libraries Government Documents Department
open access

Investigation of heat-transfer coefficients in an afterburner

Description: Report presenting an evaluation of the relative importance of heat-transfer modes in an experimental afterburner. The convective heat-transfer coefficients near the combustion-chamber outlet were determined and the effects of three radial distributions of afterburner fuel across the turbine-outlet annulus on the convective heat-transfer coefficient were examined.
Date: June 27, 1952
Creator: Koffel, William K. & Kaufman, Harold R.
Partner: UNT Libraries Government Documents Department
open access

Time-History Data of Maneuvers Performed by McDonnell F2H-2 Airplane During Squadron Operational Training

Description: Report presenting preliminary results of one phase of a control-motion study program using data obtained from 276 maneuvers performed using a McDonnell F2H-2 jet fighter airplane during normal squadron operational training. Results regarding classification of maneuvers, airspeed, load factors, sideslip angle, and maximum pitching-, rolling-, and yawing-angular-acceleration variations with indicated airspeed are provided.
Date: May 27, 1952
Creator: Huss, Carl R.; Andrews, William H. & Hamer, Harold A.
Partner: UNT Libraries Government Documents Department
open access

The Calculation of Certain Static Aeroelastic Phenomena of Wings With Tip Tanks or Boom-Mounted Lifting Surfaces

Description: Report presenting the use of the matrix-integration method for calculating static aeroelastic phenomena on a wing with concentrated aerodynamic forces at the tip due to tip tanks or boom-mounted lifting surfaces. The results indicate that the presence of a tip tank on an unswept wing tends to deteriorate its static aeroelastic characteristics and that a lift surface geared to the aileron and mounted on a boom ahead of the tip may improve the static aeroelastic characteristics to warrant conside… more
Date: August 27, 1952
Creator: Diederich, Franklin W. & Foss, Kenneth A.
Partner: UNT Libraries Government Documents Department
open access

Pressure Recovery, Drag, and Subcritical Stability Characteristics of Three Conical Supersonic Diffusers at Stream Mach Numbers From 1.7 to 2.0

Description: A study of a 20 degree and a 25 degree half-angle high mass-flow ratio conical supersonic inlet was made on a 16-inch ram jet in the 8- by 6-foot supersonic tunnel. A greater range of stable subcritical operation was obtained with the low mass-flow ratio inlets; a greater range was obtained with the 25 degree than with the 20 degree half-angle low mass-flow ratio inlet. The high mass-flow ratio inlet had the least drag.
Date: February 27, 1952
Creator: Nussdorfer, Theodore J.; Obery, Leonard J. & Englert, Gerald W.
Partner: UNT Libraries Government Documents Department
open access

Internal-liquid-film-cooling experiments with air-stream temperatures to 2000 degrees F. in 2- and 4-inch-diameter horizontal tubes

Description: Report presents the results of an investigation conducted to determine the effectiveness of liquid-cooling films on the inner surfaces of tubes containing flowing hot air. Experiments were made in 2- and 4-inch-diameter straight metal tubes with air flows at temperatures from 600 degrees to 2000 degrees F. and diameter Reynolds numbers from 2.2 to 14 x 10(5). The film coolant, water, was injected around the circumference at a single axial position on the tubes at flow rates from 0.02 to .24 pou… more
Date: May 27, 1952
Creator: Kinney, George R.; Abramson, Andrew E. & Sloop, John L.
Partner: UNT Libraries Government Documents Department
open access

Final draft for Program X descriptive criteria, architectural and structural

Description: This is an addenda to the final draft for Program X. It contains two changes one for the storage basin for discharged fuel elements and the other for a fuel element storage facility immediately adjacent to the work area. Specifications for each facility are given.
Date: March 27, 1952
Creator: Jaske, R. T.
Partner: UNT Libraries Government Documents Department
open access

Limiting Conditions for Jet Formation in High Velocity Collisions

Description: This report discusses the high-velocity collisions of two identical solid plates driven by high explosives. The collision data employs dural, mild steel, brass and lead, as well as experimenting with jetless and jet-forming collisions.
Date: March 27, 1952
Creator: Walsh, J. M.; Shreffler, R. G. & Willig, F. J.
Partner: UNT Libraries Government Documents Department
open access

Limits -- cooling water contamination

Description: The question of maximum permissible levels of fission products or corrosion products in the pile effluent water which you raised is not a simple problem that can be completely answered by a list of maximum permissible levels. This water is a complex mixture of various isotopes each of which contributes to the total hazard according to the amount present, its particular metabolic features, and its mode of radioactive decay. Unfortunately, also, application of maximum permissible limits determine… more
Date: May 27, 1952
Creator: Healy, J. W.
Partner: UNT Libraries Government Documents Department
open access

Drift Tube Model Magnet Report

Description: Early in the design of the Mark I accelerator it was decided to install magnetic lenses in the drift tubes. A number of model magnets were constructed and tested to determine the best design for these lenses. This report includes only the results of the tests on the final models of the magnets that are designed for Mark I.
Date: June 27, 1952
Creator: Sewell, D. & Parmentier, H.
Partner: UNT Libraries Government Documents Department
open access

Altitude Starting Tests of a 1000-Pound-Thrust Solid-Propellant Rocket

Description: Four solid-propellant rocket engines of nominal 1000-pound-thrust were tested for starting characteristics at pressure altitudes ranging from 112,500 to 123,000 feet and at a temperature of -75 F. All engines ignited and operated successfully. Average chamber pressures ranged from 1060 to ll90 pounds per square inch absolute with action times from 1.51 to 1.64 seconds and ignition delays from 0.070 t o approximately 0.088 second. The chamber pressures and action times were near the specificatio… more
Date: August 27, 1952
Creator: Sloop, John L.; Rollbuhler, R. James & Krawczonek, Eugene M.
Partner: UNT Libraries Government Documents Department
open access

Pressure Recovery, Drag, and Subcritical Stability Characteristics of Conical Supersonic Diffusers With Boundary-Layer Removal

Description: A study of two 20 degrees half-angle, low mass-flow ratio conical supersonic inlets with cone boundary-layer bleed was made on a 16-inch ram-jet engine in the Lewis 8- by 6-foot supersonic wind tunnel. A greater stable subcritical range of operation was obtained with the bleed inlets than with the corresponding inlet without boundary-layer bleed. The drag added by the bleed system was small.
Date: February 27, 1952
Creator: Obery, Leonard J.; Englert, Gerald W. & Nussdorfer, Theodore J.
Partner: UNT Libraries Government Documents Department
open access

Comparison of Turbojet-Engine Altitude Performance Characteristics and Ignition Limits With MIL-F-5624A Fuel, Grades JP-3 and JP-4

Description: The performance of MIL-F-5624A fuels, grades JP-3 and JP-4, was investigated in an axial-flow turbojet engine over a range of altitude conditions of 10,000 to 55,000 feet. Examination of the fuel flow, combustion efficiency, and net thrust specific fuel consumption showed the grade JP-4 fuel to be slightly inferior to the grade JP-3 fuel, although the altitude ignition limits were essentially equal for the two fuels over a range of flight Mach numbers and fuel-inlet temperatures.
Date: February 27, 1952
Creator: Braithwaite, Willis M. & Renas, Paul E.
Partner: UNT Libraries Government Documents Department
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