Resource Type
Serial/Series Title
NACA Research Memorandums
159
Atomic Energy Commission Reports
95
Hanford Works Reports
52
HW (Series)
40
North American Aviation Reports
24
AEC research and development report
20
BMI (Series)
19
Battelle Memorial Institute Reports
19
NACA Technical Reports
15
Oak Ridge National Laboratory Reports
14
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Absorption by Soil of Strontium From 216-S Crib Waste
A preliminary soil column experiment with a waste sample from the 207-S-11 well, which monitors the 216-S cribs, indicated that cesium was absorbed almost completely by the soil but that strontium breakthrough to ground water in the near future seemed likely. Accordingly, it was suggested that the 216-S wastes be discharged to a new disposal site, and that samples of the wastes which are currently being discharged to the 216-S cribs be obtained for soil absorption tests. The primary purpose of these tests was to obtain data which could be used to suggest ways and means of improving the absorption of strontium by soil from the process condensate stream (D-2_ and the cell drainage stream (D-1), both of which have been discharged to the 216-S cribs for the past several months.
Date:
February 15, 1956
Creator:
Rhodes, D. W.
Object Type:
Report
System:
The UNT Digital Library
Additional comparisons between computed and measured transonic drag-rise coefficients at zero lift for wing-body-tail configurations
From Introduction: "This report makes further comparisons of the theoretical computing method with available experimental results, showing effects of wing plan-form changes, and the effect of an airfoil-section change on a wing of given plan form."
Date:
August 15, 1955
Creator:
Holdaway, George H.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics at transonic speeds of a wing having a 45 degree sweep, aspect ratio 8, taper ratio 0.45, and airfoil sections varying from the NACA 63A010 section at the root to the NACA 63A006 section at the tip.
Report presenting an investigation in the 7- by 10-foot tunnel to determine the transonic aerodynamic characteristics of a wing with a spanwise variation in thickness ratio. The wings investigated had 45 degrees of sweepback, aspect ratio 8, taper ratio 0.45, and airfoil sections tapered from an NACA 63A010 section at the root chord to an NACA 63A006 section at the tip chord. Results regarding lift characteristics, drag characteristics, and pitching-moment characteristics are provided.
Date:
January 15, 1952
Creator:
Morrison, William D., Jr. & Fournier, Paul G.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Loads on an External Store Adjacent to a 45 Degree Sweptback Wing at Mach Numbers From 0.70 to 1.96, Including an Evaluation of Techniques Used
"Aerodynamic forces and moments have been obtained in the Langley 9- by 12-inch blowdown tunnel on an external store and on a 45 degree swept-back wing-body combination measured separately at Mach numbers from 0.70 to 1.96. The wing was cantilevered and had an aspect ratio of 4.0; the store was independently sting-mounted and had a Douglas Aircraft Co. (DAC) store shape. The angle of attack range was from -3 degrees to 12 degrees and the Reynolds number (based on wing mean aerodynamic chord) varied from 1.2 x10(6) to 1.7 x 10(6)" (p. 1).
Date:
November 15, 1955
Creator:
Guy, Lawrence D. & Hadaway, William M.
Object Type:
Report
System:
The UNT Digital Library
The Alpha Half-Life of the Isotope Pu-241
A plutonium solution of known Pu-241 content was purified by solvent extraction techniques to remove uranium and americium impurities. Portions of this purified solution were then analyzed for U-237 as a function of time. Since the growth of U-237 occurs directly by the alpha decay of Pu-241, these measurements provided sufficient data for calculation of the Pu-241 alpha half-life, which was found to be 2.91 ± 0.50 x 10⁵ years.
Date:
February 15, 1955
Creator:
Gift, M. W.
Object Type:
Report
System:
The UNT Digital Library
Altitude Free-Jet Investigation of Dynamics of a 28-Inch-Diameter Ram-Jet Engine
From Introduction: "The feasibility of closed-loop control of ram-jet-engine thrust is demonstrated in references 1 and 2. The dynamic behavior of a 28-inch-diameter ram-jet engine designed to operate in Mach number range of 2.35 to 2.70 is evaluated herein."
Date:
January 15, 1957
Creator:
Wentworth, Carl B.; Dunbar, William R. & Crowl, Robert J.
Object Type:
Report
System:
The UNT Digital Library
Altitude-performance and Reynolds number investigation of centrifugal-flow-compressor turbojet engine
From Introduction: "Altitude-chamber and wind-tunnel investigations of the performance of turbojet engines such as those reported in references 1 to 4 have shown that the conventional correction factors fail to generalize the engine performance variables at high altitudes. An investigation was therefore made at the NACA Lewis laboratory to determine the altitude performance of the J33-A-23 turbojet engine and to demonstrate the magnitude of departure of actual altitude performance from that predicted from sea-level performance."
Date:
May 15, 1951
Creator:
Wilsted, H. D. & Grey, R. E.
Object Type:
Report
System:
The UNT Digital Library
Altitude Performance of a 20-Inch-Diameter Ram-Jet Engine Investigated in a Free-Jet Facility at Mach Number 3.0
Report discussing the performance of a 20-inch-diameter ram-jet engine at Mach number 3.0 over a range of simulated altitudes from 60,500 to 66,500 feet. Information about the maximum combustor efficiency, range of exhaust-nozzle total pressures, lean blow-out, diffuser total-pressure recovery, and internal thrust coefficient is provided.
Date:
June 15, 1953
Creator:
Smolak, George R. & Wentworth, Carl B.
Object Type:
Report
System:
The UNT Digital Library
Altitude Performance of a 20-Inch-Diameter Ram-Jet Engine Investigated in a Free Jet Facility at Mach Number 3.0
Report presenting an investigation of the performance of a 20-inch-diameter ram-jet engine at Mach number 3.0 in a free-jet facility over a range of simulated altitudes. Results regarding the diffuser characteristics, combustor performance, thrust output, and operational characteristics are provided.
Date:
June 15, 1953
Creator:
Smolak, George R. & Wentworth, Carl B.
Object Type:
Report
System:
The UNT Digital Library
Altitude performance of compressor, turbine, and combustor components of 600-B9 turbojet engine
From Introduction: "The purpose of this report is (1) to describe the performance of each component over a range of altitudes, (2) to show the effect of flight conditions on operating point of each component, and (3) to summarize briefly the effects of changes in component performance with flight condition on the over-all engine performance."
Date:
March 15, 1954
Creator:
Prince, William R. & Wile, Dorwin B.
Object Type:
Report
System:
The UNT Digital Library
Altitude-Wind-Tunnel Investigation of Combustion-Chamber Performance on J47 Turbojet Engine
From Introduction: "Results are presented to indicate the effect of altitude, flight Mach number, and exhaust-nozzle-outlet area on the combustion efficiency, the losses in total pressure occurring in the combustion chamber, and the fractional loss in engine cycle efficiency resulting from combustion-chamber pressure losses. The engine cycle efficiency is also presented.These results are shown graphically as a fraction of corrected engine speed and in tabular form."
Date:
December 15, 1950
Creator:
Campbell, Carl E.
Object Type:
Report
System:
The UNT Digital Library
Ames Laboratory Quarterly Summary Research Report: July-September 1951
A report about metallurgy, chemistry, and physics of metals and alloys. Particular metals include zirconium, thorium, and vanadium metal as well as other earth metals.
Date:
November 15, 1951
Creator:
Dreeszen, W. E.
Object Type:
Report
System:
The UNT Digital Library
The Ammonium Carbonate Pressure Leaching of Uranium Ores Proposed as Feed to the Pilot Plant at Grand Junction, Colorado : Progress Report
From introduction: This is Progress report BMI-282, the first of a series covering the operation of the pressure-leaching towers for the extraction of uranium by an ammonium carbonate leach...This report discusses the data obtained from tests run to show the effects of such variables as the amount of air and carbon dioxide passed through the pulp, temperature, pressure, and concentration of ammonium carbonate and ammonium bicarbonate in the leach solution on the extraction of uranium.
Date:
June 15, 1955
Creator:
Wheeler, C. M.; Langston, B. G. & Stephens, F. M., Jr.
Object Type:
Report
System:
The UNT Digital Library
An Analytic Study of Turbojet Engine Thrust Augmentation With Liquid Hydrogen, Pentaborane, Magnesium Slurry, and JP-4 Afterburner Fuels and a 220-Second Impulse Rocket
Memorandum presenting a computation and comparison of the thrust augmentation and accompanying total fuel flow for four afterburner fuels and a rocket. Four turbojet engines burning JP-4 primary fuel and several operating conditions were selected for the analyses.
Date:
August 15, 1956
Creator:
Morris, James F.
Object Type:
Report
System:
The UNT Digital Library
Analytical investigation of single-stage-turbine efficiency characteristics in terms of work and speed requirements
From Introduction: "This report presents an analysis of the effect of variations in the work and requirements on the efficiency characteristics of single-stage, full-admission turbines."
Date:
October 15, 1956
Creator:
Stewart, Warner L.
Object Type:
Report
System:
The UNT Digital Library
Analytical procedures for the plutonium Metal Fabrication Process
A report describing a the results of a fluorimetric and volumetric method for the determination of fluoride. This method was developed for the determination of ionizable fluorine in gases in the range of 1-500ppm. This method was chosen because the determination depends on the generation of a color rather than the bleaching effect or on a change of color.
Date:
January 15, 1951
Creator:
Kendall, L. F.
Object Type:
Report
System:
The UNT Digital Library
Analytical Study of the Effect of Center-of-Gravity Position on the Response to Longitudinal Control in Landing Approaches of a Swept-Wing Airplane of Low Aspect Ratio Having No Horizontal Tail
Report presenting an investigation of the effect of reducing the static stability by a practical center-of-gravity shift in swept-wing airplanes of low aspect ratio with no horizontal tail. Results regarding relocating the center of gravity, the effect of lift due to elevator deflection, the effect of increased total elevator effectiveness, and the effect of response characteristics over long time periods are provided.
Date:
October 15, 1954
Creator:
Stone, Ralph W., Jr.
Object Type:
Report
System:
The UNT Digital Library
The Anatomy of Plasmons
From abstract: "Plamons (plasma-magnetic entities) are toroidal "packages" of plasma wrapped up in their own magnetic field. Experimental evidence for the existence of plasmons is adduced and theoretical considerations concerning their various types and their stability are discussed."
Date:
November 15, 1955
Creator:
Bostick, W. H.
Object Type:
Report
System:
The UNT Digital Library
Apparent viscosity of neutralized and concentrated raw slurry : TBP HW-no. 4 and HW flowsheet
Report describing how the neutralized aqueous waste from the TBP Metal Recovery Process will be concentrated by evaporation to minimize the requirements for underground storage tank capacity.
Date:
August 15, 1950
Creator:
Allen, A. W. & Harmon, M. K.
Object Type:
Report
System:
The UNT Digital Library
The Application of Nuclear Track Emulsions to the Analysis of Urine for very Low Level Plutonium
The following document analyzes plutonium in urine which uses nuclear track film for evaluation of the quantity of separated plutonium.
Date:
November 15, 1951
Creator:
Schwendiman, L. C.; Healy, John W. & Reid, D. L.
Object Type:
Report
System:
The UNT Digital Library
An Application of the Concepts of Particle Packing to the Consolication of Silicon Carbide Powders
From introduction: Silicon carbide is being considered as a basis material for nonmetallic fuel elements because of its high thermal conductivity, low nuclear cross section, high resistance to thermal rupture, and high degree of stability at high temperature in air. A requirement of the fuel elements is that they be thin and have as low porosity as possible. One shape of element under consideration is 0.050 to 0.070 inch thick by a few inches in width and breadth.
Date:
August 15, 1952
Creator:
Harman, Cameron G.; Shinn, J., Jr. & Wagner, H. E.
Object Type:
Report
System:
The UNT Digital Library
Application of Theodorsen's propeller theory to the calculation of the performance of dual-rotating propellers
Report presenting the use of Theodorsen's propeller theory to calculate the performance of a dual-rotating propeller with nonideal load distributions. Results regarding the propeller characteristics were made for several blade-angle settings and flight Mach numbers.
Date:
March 15, 1951
Creator:
Gilman, Jean, Jr.
Object Type:
Report
System:
The UNT Digital Library
Applications of power spectral analysis methods to maneuver loads obtained on jet fighter airplanes during service operations
Report presenting power spectral densities of normal load factor obtained for two service operational training flights of a Republic F-84G airplane and three service operational training flights of a North American F-86A airplane in order to indicate the load-factor frequency content and possible uses of power spectral methods in analyzing maneuver load data. Results regarding the spectra of the two different planes, an analytical representation of maneuver load spectrum, and probability distributions are provided.
Date:
January 15, 1957
Creator:
Mayer, John P. & Hamer, Harold A.
Object Type:
Report
System:
The UNT Digital Library
Approximate analysis of effects of large deflections and initial twist on torsional stiffness of a cantilever plate subjected to thermal stresses
From Summary: "An approximate analysis of the nonlinear effects of initial twist and large deflections on the torsional stiffness of a cantilever plate subjected to a nonuniform temperature distribution is presented. The Von Karman large-deflection equations are satisfied through the use of a variational principle. The results show that initial twist and applied moments can have significant effects on the changes in stiffness produced by nonuniform heating, particularly in the region of the buckling temperature difference. Results calculated by this approximate analysis are in satisfactory agreement with measured torsional deformations and changes in natural frequency."
Date:
May 15, 1957
Creator:
Heldenfels, Richard R. & Vosteen, Louis F.
Object Type:
Report
System:
The UNT Digital Library