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The Distribution of Impurities in the Ether Extraction Process

Description: When uranium is purified by the ether extraction method, black oxide is dissolved in nitric acid and ether is added; an ether layer containing uranium and an aqueous layer containing uranium and impurities are obtained. The distribution of some impurities between the two phases and the effect of such impurities on the extraction process were studied. the processing required in the preparation of pure uranyl nitrate might be decreased if, instead of uranosic oxide, sodium diuranate was used as a… more
Date: January 22, 1947
Creator: Brimm, E. O., Dr. & Mohr, P
Partner: UNT Libraries Government Documents Department
open access

Drag Measurements at Transonic Speeds of NACA 65-009 Airfoils Mounted on a Freely Falling Body to Determine the Effects of Sweepback and Aspect Ratio

Description: From Summary: "Drag measurements at transonic speeds on rectangular airfoils and on airfoils swept back 450 are reported. These airfoils, which were mounted on cylindrical test bodies, are part of a series being tested in free drops from high altitude to determine the effect of variation of basic airfoil parameters on airfoil drag characteristics at transonic speeds. These rectangular and swept-back airfoils had the same span, airfoil section (NACA 65-009), and chord perpendicular to the leadin… more
Date: January 22, 1947
Creator: Mathews, Charles W. & Thompson, Jim Rogers
Partner: UNT Libraries Government Documents Department
open access

Effect of Exhaust Pressure on the Cooling Characteristics of a Liquid-Cooled Engine

Description: "Data for a liquid-cooled engine with a displacement volume of 1710 cubic inches were analyzed to determine the effect of exhaust pressure on the engine cooling characteristics. The data covered a range of exhaust pressures from 7 to 62 inches of mercury absolute, inlet-manifold pressures from 30 to 50 inches of mercury absolute, engine speeds from 1600 to 3000 rpm, and fuel-air ratios from 0.063 to 0.100. The effect of exhaust pressure on engine cooling was satisfactorily incorporated in the N… more
Date: January 22, 1947
Creator: Doyle, Ronald B. & Desmon, Leland G.
Partner: UNT Libraries Government Documents Department
open access

Performance of the 19XB 10-Stage Axial-Flow Compressor with Altered Blade Angles

Description: "Previous performance data of the 19XB axial-flow compressor indicated that the outlet guide vanes and possibly the inlet guide vanes were stalling. Calculations were made to determine if these adverse conditions could be eliminated and if the manufacturer's design specifications could be more nearly approached by altering the blade angles of the first few compression stages as well as the outlet guide vanes. With the blade angles altered, experimental data were taken at compressor speeds of 85… more
Date: January 22, 1947
Creator: Downing, Richard M.; Finger, Harold B. & Roepcke, Fay A.
Partner: UNT Libraries Government Documents Department
open access

Control Chart Method Applied to Errors in Radioactive Counting

Description: Abstract: The Control Chart statistical methods, developed by Showhart for the control of quality of manufactured products, are applied to the control of Geiger-Miller counting instruments. Experiments are reported to show the use to the Control Chart method for detecting disturbances in instrumental behavior and for detecting radioactive effects so weak that they are near the limit of detection of the instruments. As a corollary, the control chart can be used to reduce to its practical limit t… more
Date: February 22, 1947
Creator: Schlecht, W. G.
Partner: UNT Libraries Government Documents Department
open access

Correlation of the Trim Limits of Stability Obtained for a PB2Y-3 Flying Boat and a 1/8-Size Powered Dynamic Model

Description: Tests of a PB2Y-3 flying boat were made at the U.S. Naval Air Station, Patuxent River, Md., to determine its hydrodynamic trim limits of stability. Corresponding tests were also made of a 1/8-size powered dynamic model of the same flying boat in Langley tank no. 1. During the tank tests, the full-size testing procedure was reproduced as closely as possible in order to obtain data for a direct correlation of the results. As a nominal gross load of 66,000 pounds, the lower trim limits of the full… more
Date: April 22, 1947
Creator: Garrison, Charlie C.; Goldenbaum, David M. & Hacskaylo, Andrew
Partner: UNT Libraries Government Documents Department
open access

Drag characteristics of rectangular and swept-back NACA 65-009 airfoils having various aspect ratios as determined by flight tests at supersonic speeds

Description: Report presenting tests to determine the effect of sweepback angle and aspect ratio on the drag at supersonic speeds of wings of NACA 65-009 airfoil section. The current report is part of a bigger investigation and includes results for aspect ratios of 3.8 and 5.0. Results regarding the drag coefficient and general effect of aspect ratio are provided.
Date: April 22, 1947
Creator: Tucker, Warren A. & Nelson, Robert L.
Partner: UNT Libraries Government Documents Department
open access

A Fast Coincidence Circuit with Pulse Height Selection

Description: Abstract: The output signal of a linear accelerator may have a rise time of 1-2 x 10[minus]7 seconds. Therefore, the output of a pulse height selector operating on this signal has a variation of delay from the original signal of about this amount. In the instrument to be described in this technical report this difficulty is largely resolved.
Date: April 22, 1947
Creator: Bell, P. B.; DeBenedetti, Sergio & Francis, J. B., Jr.
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Downwash at the Probable Tail Location Behind a High-Aspect-Ratio Wing in the Langley 8-Foot High-Speed Tunnel

Description: Report presenting measurements downwash angles behind a model of a high-aspect-ratio wing at points near the probable tail location at Mach numbers up to 0.89 in the high-speed tunnel. The model has an NACA 65-210 section, an aspect ratio of 9.0, a taper ratio of 2.5:1, no twist, dihedral, or sweepback. Results regarding experimental data and comparison of experimental and calculated results are provided.
Date: April 22, 1947
Creator: Whitcomb, Richard T.
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Aerodynamic Characteristics of an 0.08-Scale Model of the Chance Vought XF7U-1 Airplane in the Langley High-Speed 7- by 10-Foot Tunnel. Part 4 - Aileron Characteristics TED No. NACA DE308, Part 4, Aileron Characteristics, TED No. NACA DE308

Description: Tests have been conducted in the Langley high-speed 7- by 10-foot tunnel over a Mach number range from 0.40 to 0.91 to determine the stability and control characteristics of an 0.08-scale model of the Chance Vought XF7U-1 airplane. The aileron characteristics of the complete model are presented in the present report with a very limited analysis of the results.
Date: August 22, 1947
Creator: Goodson, Kenneth W. & Myers, Boyd C., II
Partner: UNT Libraries Government Documents Department
open access

100 Areas technical activities report: Engineering, August 1947

Description: There were seven charges of metal inspected during the month for corrosion and blistering studies. There were no unusual cases of blistering noted and the corrosion rates were normal for this time of year. Borescopic examination of the graphite packing around the ``B`` Hole in the F Pile revealed that the graphite is no more severely cracked than in the D Pile when it was inspected about a year ago. Examination of the graphite at the downstream and of Tube 1385-D did not indicate that any damag… more
Date: September 22, 1947
Creator: Woods, W. K.
Partner: UNT Libraries Government Documents Department
open access

Preliminary Report on Existing Active Particle Hazard-200 Areas

Description: "Recent surveys by the Health Instrument Section have disclosed the presence of many small radioactive spots on ground surfaces in the T and B plant areas. Investigation has shown that representative samples of the spots when mechanically separated invariably end in a single radioactive particle."
Date: October 22, 1947
Creator: Mickelson, M. L.
Partner: UNT Libraries Government Documents Department
open access

Some Tests and Calculations Pertaining to the Dive Path and to Wing and Tail Loads in the Accident to Eastern Airlines C54B Airplane, NC-88814, Near Bainbridge, Maryland, May 30, 1947

Description: "Several dive paths were calculated for a C54 airplane starting from level flight at an altitude of 4000 feet and from an initial indicated airspeed of 200 miles per hour. The results show that, within the limits of the possible paths permitted by the evidence of the crash at Bainbridge, the speed of impact would be about 370 miles per hour and the time to crash would be between 12 1/2 and 15 1/2 seconds. Tail load calculations indicate that, with moderate negative acceleration of the airplane,… more
Date: October 22, 1947
Creator: Rhode, Richard V.; Stokke, Allen R. & Rogin, Leo
Partner: UNT Libraries Government Documents Department
open access

Preliminary Results of Altitude-Wind-Tunnel Investigation of X24C-4B Turbojet Engine. 4 - Performance of Modified Compressor, Part 4, Performance of Modified Compressor

Description: The performance of the 11-stage axial-flow compressor, modified to improve the compressor-outlet velocity, in a revised X24C-4B turbojet engine is presented and compared with the performance of the compressor in the original engine. Performance data were obtained from an investigation of the revised engine in the MACA Cleveland altitude wind tunnel. Compressor performance data were obtained for engine operation with four exhaust nozzles of different outlet area at simulated altitudes from 15,OO… more
Date: December 22, 1947
Creator: Thorman, H. Carl & Dupree, David T.
Partner: UNT Libraries Government Documents Department
open access

Tests of the AN/SPS-1 Radar Antenna in the Langley Full-Scale Tunnel

Description: Tests have been conducted to determine the drive-motor torque and the static force and moment characteristics of the AN/SPS-1 radar antenna. Shifting the longitudinal position of the antenna had very little effect on the drive-motor torque, which reached a maximum value expressed in terms of dynamic pressure (T/q)(sub max) of 1.15 at an azimuth angle of 245. The maximum observed values of rolling, pitching, and yawing moments in terms of dynamic pressure are -29.0, 66.6, and 13.4, respectively.
Date: December 22, 1947
Creator: May, Ralph W., Jr.
Partner: UNT Libraries Government Documents Department
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