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The Analysis of TBP Process Streams for Calcium with the Flame Photometer

Description: Summary: A method was found for determining calcium concentrations in TBP process streams in spite of serious interferences bysodium, ferrous, uranyl, sulfate, phosphate, and sulfamate ions as well as by TBP. The precision attainable varied from sample to sample, depending upon its composition. In general, errors of 20% or greater occurred. The smallest determinable amount of calcium was about 10 mg/1.
Date: February 20, 1953
Creator: Brite, D. W.
Item Type: Refine your search to only Report
open access

Analytical comparison of turbine-blade cooling systems designed for a turbojet engine operating at supersonic speed and high altitude 1: liquid-cooling systems

Description: Report presenting an investigation of the influence of high-altitude supersonic flight on the operation and effectiveness of turbine-blade liquid-cooling systems for application in turbojet engines in guided missiles and in supersonic aircraft. The problems encountered in liquid-cooling systems were investigated with reference to several specific designs for alternate heat-rejection mediums.
Date: February 20, 1953
Creator: Schramm, Wilson B.; Nachtigall, Alfred J. & Arne, Vernon L.
Item Type: Refine your search to only Report
open access

BEVATRON RESEARCH MEETING III - BEVATRON THEORY

Description: Despite the essentially independent development of the Cosmotron and Bevatron, these two accelerators have general specifications which are the same within a factor of 2-3 in their pertinent characteristics. An electron analogue of the Bevatron would be an electron synchrotron operating in the 5 kev to 3 Mev range.
Date: October 20, 1953
Creator: Smith, Lloyd
Item Type: Refine your search to only Report
open access

Compressible-Flow Solutions for the Actuator Disk

Description: Report presenting generalized solutions for the actuator disk in subsonic compressible flow and the compressible- and incompressible-flow phenomena are compared. Results regarding the ideal solutions of flow variables, effect of additional losses, and actuator disks in tandem are provided. Large differences in flow variables were observed across the actuator disk.
Date: March 20, 1953
Creator: Delano, James B. & Crigler, John L.
Item Type: Refine your search to only Report
open access

Effect of rotor-and stator-blade modifications on surge performance of an 11-stage axial-flow compressor 1: original production compressor of XJ40-WE-6 engine

Description: Report presenting an investigation to increase the compressor surge-limit pressure ratio of the XJ40-WE-6 turbojet engine at high equivalent speeds. The two compressor modifications investigated included twisting rotor blades to change blade section angles and inserting new stator diaphragms with different blade angles. Results regarding the effect of surge limit on engine performance, performance map of original compressor with mixer, effect of blade modifications on surge line, effect of mixe… more
Date: May 20, 1953
Creator: Finger, Harold B.; Essig, Robert H. & Conrad, E. William
Item Type: Refine your search to only Report
open access

Experimental Investigation of Radome Icing and Icing Protection

Description: Memorandum presenting an investigation conducted in the icing research tunnel to determine the icing characteristics, the effects of icing on radar operation, and the protection requirements for two radome configurations. The radomes were for the F-89 airplane and were investigated at airspeeds up to 290 miles per hour, air total temperatures from -15 to 20 degrees Fahrenheit, water contents up to 1.0 gram per cubic meter, and angles of attack of 0 and 4 degrees.
Date: January 20, 1953
Creator: Lewis, James P. & Blade, Robert J.
Item Type: Refine your search to only Report
open access

Flight Determination of the Static Longitudinal Stability Boundaries of the Bell X-5 Research Airplane with 59 Degrees Sweepback

Description: "During the flight program on the Bell X-5 airplane with 59 degrees sweepback to determine the practical Mach number and normal-force coefficient limits of this configuration, a reduction in static longitudinal stability was encountered in maneuvering flight. A determination of the boundary for reduction of longitudinal stability extending to a Mach number of 0.98 is presented in this paper. A reduction of static longitudinal stability existed for all elevator and all stabilizer-executed maneuv… more
Date: February 20, 1953
Creator: Finch, Thomas W. & Walker, Joseph A.
Item Type: Refine your search to only Report
open access

Hanford Atomic Products Operation monthly report, April 1953

Description: This is a progress report of the production reactors on the Hanford Reservation for the month of April 1951. This report takes each division (e.g., manufacturing, medical, accounting, occupational safety, security, reactor operations, etc.) of the site and summarizes its accomplishments and employee relations for that month.
Date: May 20, 1953
Creator: McCune, F. K.
Item Type: Refine your search to only Report
open access

Hanford Atomic Products Operation monthly report, July 1953

Description: This document presents a summary of work and progress at the Hanford Engineer Works for July 1953. The report is divided into sections by department. A plant wide general summary is included at the beginning of the report, after which the departmental summaries begin. The Manufacturing Department reports plant statistics, and summaries for the Metal Preparation, Reactor and Separation sections. The Engineering Department`s section summaries work for the Technical, Design, and Project Sections. … more
Date: August 20, 1953
Item Type: Refine your search to only Report
open access

Hanford Atomic Products Operation monthly report, October 1953

Description: This document presents a summary of work and progress at the Hanford Engineer Works for October 1953. The report is divided into sections by department. A plant wide general summary is included at the beginning of the report, after which the departmental summaries begin. The Manufacturing Department reports plant statistics, and summaries for the Metal Preparation, Reactor and Separation sections. The Engineering Department`s section summaries work for the Technical, Design, and Project Section… more
Date: November 20, 1953
Item Type: Refine your search to only Report
open access

Investigation of the Effects of Leading-Edge Flaps on the Aerodynamic Characteristics in Pitch at Mach Numbers From 0.40 to 0.93 of a Wing-Fuselage Configuration With a 45 Degree Sweptback Wing of Aspect Ratio 4

Description: Report presenting an investigation to determine the effects of a number of leading-edge flaps on the aerodynamic characteristics in pitch of a wing-fuselage configuration with a 45 degree sweptback wing. All of the flaps were found to reduce the drag in the medium lift range , but there were no significantly large effects on the lift characteristics for any of the arrangements studied.
Date: August 20, 1953
Creator: Spreemann, Kenneth P. & Alford, William J., Jr.
Item Type: Refine your search to only Report
open access

Large-scale flight measurements of zero-lift drag and low-lift longitudinal characteristics of a diamond-wing-body combination at Mach numbers from 0.725 to 1.54

Description: Report presenting a large-scale diamond-wing-body configuration flown at a range of Mach and Reynolds numbers. The model had a diamond-plan-form wing with an NACA 65A003 airfoil section, a total aspect ratio of 2.31, and 0 degrees sweep of the midchord. Results regarding zero-lift drag and low-lift longitudinal characteristics are provided.
Date: April 20, 1953
Creator: Wallskog, Harvey A. & Morrow, John D.
Item Type: Refine your search to only Report
open access

Longitudinal Stability, Control Effectiveness, and Drag Characteristics at Transonic Speeds of a Rocket-Propelled Model of an Airplane Configuration Having an Unswept Tapered Wing of Aspect Ratio 3.0 and NACA 65A004.5 Airfoil Sections

Description: Report presenting an investigation of an airplane configuration with an unswept tapered wing of aspect ratio 3.0 with NACA 65A004.5 airfoil sections. Static and dynamic longitudinal stability, control effectiveness, and drag characteristics are included. The results of this investigation are compared to similar models with wings of the same plan-form dimensions but with hexagonal airfoil sections.
Date: January 20, 1953
Creator: McFall, John C., Jr. & Hollinger, James A.
Item Type: Refine your search to only Report
open access

Low-Speed Investigation of the Aerodynamic, Control, and Hinge-Moment Characteristics of Two Types of Controls on a Delta-Wing-Fuselage Model With and Without Nacelles

Description: Report presenting an investigation to determine the low-speed aerodynamic and control characteristics of a 3-percent-thick 60 degree sweptback delta-wing-fuselage combination with half-delta tip controls and horn-balance-type controls. Testing was also conducted with chord-plate-mounted nacelles located at three positions on the wing. Information regarding the longitudinal, lateral, and hinge-moment characteristics is also provided.
Date: May 20, 1953
Creator: Scallion, William I.
Item Type: Refine your search to only Report
open access

Low-speed lateral control characteristics of an unswept wing with hexagonal airfoil sections and aspect ratio 4.0 at a Reynolds number of 6.2 x 10(exp 6)

Description: Report presenting a lateral-control investigation in the 19-foot pressure tunnel of an unswept wing with 6-percent-thick hexagonal airfoil sections, aspect ratio 4.0, and taper ratio 0.625. The wing was mounted on a circular fuselage with a fineness ratio of 10 to 1.
Date: March 20, 1953
Creator: Hadaway, William M.
Item Type: Refine your search to only Report
open access

The low-speed lift and pitching moment characteristics of a 45 degree sweptback wing of aspect ratio 8 with and without high-lift and stall-control devices as determined from pressure distribution at a Reynolds number of 4.0 x 10(exp 6)

Description: A determination of the manner in which the lift and pitching-moment characteristics of a 45 degree sweptback wing are influenced by high-lift and stall-control devices by using detailed pressure-distribution measurements. The results indicate that the instability of the basic wing was due to flow separation which originated over the outer 4 percent of the wing semispan. The stability of the wing was improved through the use of upper-surface fences or leading-edge flaps.
Date: January 20, 1953
Creator: Bollech, Thomas V. & Hadaway, William M.
Item Type: Refine your search to only Report
open access

Maximum Altitude and Maximum Mach Number Obtained With the Modified Douglas D-558-II Research Airplane During Demonstration Flights

Description: "Flights to explore the high altitude and Mach number regions were made with the Douglas D-558-II research airplane in August 1951. Maximum pressure altitude recorded was 77,500 feet and the maximum geometric altitude obtained from radar data was 79,500 feet above sea level. The maximum Mach number obtained was 1.87. When a standard atmosphere is assumed, this value represents a true airspeed of 1238 miles per hour; or at the existing temperature, 3 degrees Fahrenheit above standard, this repre… more
Date: April 20, 1953
Creator: Dahlen, Theodore E.
Item Type: Refine your search to only Report
open access

Measurements of Water Lattices

Description: A series of measurements of ε in slightly enriched uranium, light water lattices is presently under way at Brookhaven. Figure 1 shows ε as a function of water-to-metal ratio for .600" diameter rods, of 1.3% enrichment. Because of interaction between neighboring groups of rods, ε increases rapidly as the water-to-metal ratio decreases.
Date: July 20, 1953
Creator: Kouts, Herbert & Chernick, Jack
Item Type: Refine your search to only Report
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