Resource Type
Serial/Series Title
NACA Research Memorandums
173
Atomic Energy Commission Reports
61
NACA Technical Reports
30
Hanford Works Reports
20
HW (Series)
16
Oak Ridge National Laboratory Reports
15
University of California Radiation Laboratory Reports
12
AEC research and development report
6
AECU (Series)
6
BNL (Series)
6
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331 Matching Results
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Influence of Fluorine Substitution on the Properties of Metal Chelate Compounds
From introduction: "This is the first of three articles dealing with the influence of fluorine substitution in the ligand on the properties of metal chelate compounds. Although the primary purpose of this project was to study the influence of fluorine substitution on the properties -- particularly light absorption -- of uranyl compounds, copper chelates were chosen for preliminary study as model substances, because they are easily prepared."
Date:
June 9, 1955
Creator:
Belford, R. Linn; Martell, Arthur E. & Calvin, Melvin, 1911-1997
Object Type:
Report
System:
The UNT Digital Library
Line Broadening by Electrons : the Validity of Simple Theories
A comparison of the simple impact theories of line broadening by electrons with the detailed computations of Kivel, Bloom, and Margenau.
Date:
May 9, 1955
Creator:
Meyerott, Roland Edward & Margenau, Henry, 1901-1997.
Object Type:
Report
System:
The UNT Digital Library
Low-Pressure Performance of a Tubular Combustor With Gaseous Hydrogen
Memorandum presenting an investigation to determine the combustion performance characteristics of gaseous hydrogen fuel in a single tubular turbojet combustor. The combustor was operated over a range of inlet-air pressures from 3.3 to 14.3 inches of mercury absolute. Results regarding stability limits and combustion efficiency are provided.
Date:
May 9, 1955
Creator:
Jonash, Edmund R.; Smith, Arthur L. & Hlavin, Vincent F.
Object Type:
Report
System:
The UNT Digital Library
Higher harmonics of Radial Vibrations in Short Hollow Cylinders of Barium Titanate
This paper discusses the forbidden and allowed harmonics of a hollow cylinder of barium titanate vibrating in the radial mode.
Date:
March 9, 1955
Creator:
Stephenson, C.V.
Object Type:
Report
System:
The UNT Digital Library
Over-All Performance of J65-B3 Turbojet Engine for Reynolds Number Indices from 0.8 to 0.2
"The steady-state over-all performance characteristics of the J65-B3 turbojet engine were determined in an altitude test chamber for four exhaust-nozzle areas at Reynolds number indices of 0.8, 0.4, and 0.2. This range of Reynolds number indices corresponds to a range of altitudes from about sea level to 51,500 feet at a flight Mach number of 0.8. Generalized data are presented to allow calculation of engine performance at any flight condition corresponding to a Reynolds number index within the range investigated" (p. 1).
Date:
March 9, 1955
Creator:
Fenn, David B. & Jones, William L.
Object Type:
Report
System:
The UNT Digital Library
Suggested Uses of Cycloidal-Trajectory Particle Spectrometers in Nuclear Research
From abstract: "The motion of a charged particle in a region of crossed electric and magnetic fields is discussed... Possible applications of such a system to various problems in nuclear research are suggested and it is shown to be possible in principle to measure the kinetic energy, mass, and ionic charge of various nuclear-reaction products and to separate various short-lived products for rapid examination. Two different devices are proposed. The application of the technique to investigation of the fission process is specifically discussed."
Date:
March 9, 1955
Creator:
Stevenson, Peter Cooper
Object Type:
Report
System:
The UNT Digital Library
Altitude-Test-Chamber Investigation of the Endurance and Performance Characteristics of the J65-W-7 Engine at a Mach Number of 2.0
"An investigation of the endurance characteristics, at high Mach number, of the J65-W-7 engine was made in an altitude chamber at the Lewis laboratory. The investigation was made to determine whether this engine can be operated at flight conditions of Mach 2 at 35,000-feet altitude (inlet temperature, 250 F) as a limited-service-life engine. Failure of the seventh-stage aluminum compressor blades occurred in both engines tested and was attributed to insufficient strength of the blade fastenings at the elevated temperatures" (p. 1).
Date:
February 9, 1955
Creator:
Biermann, A. E. & Braithwaite, Willis M.
Object Type:
Report
System:
The UNT Digital Library
Composition of vapors from boiling nitric acid solutions
From abstract: "The composition of vapors from aqueous nitric acid solutions boiling at 200 mm mercury total pressure is established for solutions containing between - and 67.5 w/o nitric acid. The volatility characteristics of low concentrations of chloride in the same concentration range of nitric acid have been measured in solutions boiling at 200 mm mercury. The effects of chloride concentration and pressure of boiling are evaluated. A spectrophotometric method of the determination of chloride in nitric acid solutions is described."
Date:
February 9, 1955
Creator:
Crooks, R. C.; Wilson, R. Q.; Bearse, A. E. & Filbert, Robert B.
Object Type:
Report
System:
The UNT Digital Library
Analytical applications of refractive index
Report detailing the refractive index of solutions of uranyl nitrate, nitric acid and aluminum nitrate. This report builds upon preliminary data and a brief discussion that from a previous report. This report covers more accurate and detailed data that had be accumulated following the initial report.
Date:
January 9, 1955
Creator:
Burger, L. L.
Object Type:
Report
System:
The UNT Digital Library
Altitude-chamber investigation of J73-GE-1A turbojet engine component performance
Report presenting an investigation to determine the altitude performance characteristics of a J73-GE-1A turbojet engine conducted in an altitude chamber. The engine had a ten-percent oversize turbine-nozzle are compared with the production J73 engine. Results regarding radial pressure and temperature profiles, compressor performance, combustor performance, turbine performance, and tail-pipe-diffuser and exhaust-nozzle performance.
Date:
December 9, 1954
Creator:
Campbell, Carl E. & Sobolewski, Adam E.
Object Type:
Report
System:
The UNT Digital Library
Altitude Performance Characteristics of the J73-GE-1A Turbojet Engine
From Introduction: "The over-all altitude-performance characteristics of this engine are reported herein, and the component performance characteristics are given in reference 1. The data are presented in the form of engine pumping characteristics to allow accurate calculation of engine performance at any operating or flight condition within the range covered by the experimental data. A curve is also presented that will allow determination of thrust in flight by the measurement of ambient static pressure and total pressure in the exhaust nozzle."
Date:
December 9, 1954
Creator:
Campbell, Carl E. & Conrad, E. William
Object Type:
Report
System:
The UNT Digital Library
High-Altitude Performance of an Experimental Turbular Prevaporizing Combustor
Memorandum presenting an investigation of an experimental tubular combustor that provides for prevaporizing and premixing of the fuel with a part of the air before its introduction into the combustion zone. Combustion efficiency and total-pressure loss data are presented for three configurations selected from a total of 43 different modifications investigated. Results regarding the combustor development, comparison of liquid and gaseous fuel, combustor total-pressure losses, combustor-outlet temperature distribution, and evaluation of experimental prevaporizing combustors are provided.
Date:
December 9, 1954
Creator:
Butze, Helmut F.
Object Type:
Report
System:
The UNT Digital Library
Investigation of compressible flow mixing losses obtained downstream of a blade row
Report presenting an investigation conducted to determine the importance of the mixing loss downstream of a blade row with respect to blade profile loss for compressible flow conditions. Theoretical and experimental results and the application of mixing loss results to the example transonic turbine are provided.
Date:
December 9, 1954
Creator:
Stewart, Warner L.
Object Type:
Report
System:
The UNT Digital Library
Method of designing corrugated surfaces having maximum cooling effectiveness within pressure-drop limitations for application to cooled turbine blades
Report presenting a method using charts for the systematic determination of a corrugation geometry configuration which, for a specific application to an air-cooled turbine blade, gives the required amount of blade temperature reduction using the minimum amount of coolant flow within pressure-drop limitations. A numerical example is included to illustrate the use of the method.
Date:
December 9, 1954
Creator:
Slone, Henry O.; Hubbartt, James E. & Arne, Vernon L.
Object Type:
Report
System:
The UNT Digital Library
Physical Studies of Cell Division: Statistical Fluctuations; Effects Due to X-Radiation, Temperature, and Hydrostatic Pressure
Thesis discussing "a technique for determining the generation times of individual yeast cells...the effect of x-radiation on the generation times of individual cells and their progeny..." and "attempts to synchronize cell division in a population of cells."
Date:
December 9, 1954
Creator:
Burns, Victor Will
Object Type:
Thesis or Dissertation
System:
The UNT Digital Library
Permeability and Strength Measurements on Sintered, Porous, Hollow Turbine Blades Made by the American Electro Metal Corporation under Office of Naval Research Contract N-ONR-295 (01)
From Summary: "An experimental investigation was made to determine the permeability and strength characteristics of a number of sintered, porous, hollow turbine rotor blades and to determine the effectiveness of the blade fabrication method on permeability control. The test blades were fabricated by the American Electro Metal Corporation under a contract with the Office of Naval Research, Department of the Navy, and were submitted to the NACA for testing. Of the 22 test blades submitted, ten were sintered but not coined, five were sintered and coined, and seven were sintered and not coined but contained perforated reinforcements integral with the blade shells. Representative samples of each group of blades were tested."
Date:
November 9, 1954
Creator:
Richards, Hadley T. & Livingood, John N. B.
Object Type:
Report
System:
The UNT Digital Library
An Investigation in the Ames 40- by 80-Foot Wind Tunnel of a YT-56A Turboprop Engine Incorporating a Decoupler and a Controlled-Feathering Device
"An investigation of a decoupler and a controlled-feathering device incorporated with the YT-56A turboprop engine has been made to determine the effectiveness of these devices in reducing the high negative thrust (drag) which accompanies power failure of this type of engine. Power failures were simulated by fuel cut-off, both without either device free to operate, and with each device free to operate singly. The investigation was made through an airspeed range from 50 to 230 mph" (p. 1).
Date:
September 9, 1954
Creator:
Rogallo, Vernon L.; Yaggy, Paul F. & McCloud, John L., III
Object Type:
Report
System:
The UNT Digital Library
Self-Shielding Measurements in PPA-20
From Introduction: "The self-shielding characteristics of a number of absorbers and of U-235 and U-238 have been investigated in PPA-20 (66°). Most of the measurements have been made in Ring 3 at the core mid-plane. The foil doubling technique was employed. Particular attention was given to 'thin' foil regions for the purpose of extrapolating the data to zero thickness."
Date:
September 9, 1954
Creator:
King, J. S.
Object Type:
Report
System:
The UNT Digital Library
Color Centers Induced in Al2O3 by Reactor and Gamma-ray Irradiation
The absorption bands induced in α-Al2O3 by gamma and reactor irradiation have been studied. The slight coloration due to γ-rays saturates. Bands specific to reactor irradiation have been found and their growth studied.
Date:
August 9, 1954
Creator:
Levy, Paul, W. & Dienes, G. J.
Object Type:
Report
System:
The UNT Digital Library
Analysis of rocket, ram-jet, and turbojet engines for supersonic propulsion of long-range missiles 1: rocket-engine performance
Report presenting theoretical performance characteristics and estimates of effective specific impulse and weight for rocket engines serving a main and booster power plants for missiles. The fuels used included ammonia-fluorine and JP4-oxygen propellants. At extremely high altitudes, the specific impulse depends primarily on the expansion ratio.
Date:
July 9, 1954
Creator:
Huff, Vearl N. & Kerrebrock, Jack
Object Type:
Report
System:
The UNT Digital Library
Preliminary investigation of pumping and thrust characteristics of full-size cooling-air ejectors at several exhaust-gas temperatures
Report presenting an experimental investigation to determine the performance of seven full-size ejector configurations over a range of secondary to primary air-flow ratios, primary total- to ambient-pressure ratios, and primary gas temperatures. Results regarding primary-nozzle performance, ejector performance, typical ejector characteristics, effect of operating temperatures on ejector flow characteristics, and effect of geometry on ejector performance are provided.
Date:
April 9, 1954
Creator:
Greathouse, W. K.
Object Type:
Report
System:
The UNT Digital Library
A Transonic Wind-Tunnel Investigation of the Static Lateral, Directional, and Longitudinal Stability Characteristics of the Martin B-61A Missile (Matador)
"The static lateral, directional, and longitudinal stability characteristics of a 0.06-scale model of the Martin B-61A missile (Matador) were investigated in the Langley 8-foot transonic tunnel at Mach numbers from 0.80 t o 1.12. Six-component force and moment data were obtained from strain-gage measurements. The characteristics of a spoiler and of wing-tip end plates were also investigated. The Reynolds number of the tests based on the mean aerodynamic chord of the wing was approximately 1.6 X 10(exp 6)" (p. 1).
Date:
April 9, 1954
Creator:
Luoma, Arvo A.
Object Type:
Report
System:
The UNT Digital Library
The Effects of Circular End Plates on the Lift, Drag, and Pitching Moment at Subsonic and Supersonic Speeds on a Modified Triangular Wing Having an Aspect Ratio of 2, a Taper Ratio of 0.33, and a 45 Degree Swept Leading Edge
Memorandum presenting an investigation made of the effects of circular end plates on the aerodynamic characteristics of a modified triangular wing of aspect ratio 2 and taper ratio 0.33. The experimental results show that the addition of end plates produces so slight a difference in the total change in static longitudinal stability with Mach number in the range from 0.6 to 1.9 that no beneficial effects on the trim drag may be realized.
Date:
March 9, 1954
Creator:
Petersen, Robert B.
Object Type:
Report
System:
The UNT Digital Library
The Effects of Horizontal-Tail Height and a Partial-Span Leading-Edge Extension on the Static Longitudinal Stability of a Wing-Fuselage-Tail Combination Having a Sweptback Wing
Memorandum presenting an investigation made to valuate the effects of vertical height of the horizontal tail on the static longitudinal stability of a model with a wing with 35 degrees of sweepback, an aspect ratio of 4.5, a taper ratio of 0.5, and NACA 64A010 sections. The investigation also included the effects of adding a partial-span, leading-edge chord extension to the outer portions of the wing. Results regarding the effect of tail height, wing-wake and local downwash measurements, and effect of a leading-edge extension are provided.
Date:
March 9, 1954
Creator:
Bandettini, Angelo & Selan, Ralph
Object Type:
Report
System:
The UNT Digital Library