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open access

17-keV x-ray output of plutonium

Description: In the production of plutonium in a reactor, plutonium-238, 240, and 241 are formed as well as Pu{sup 239}. It is well known that the specific alpha activity of the plutonium varies as the percentages of these isotopes are changed. Kinderman, et al have worked out the relationship between isotopic content and MWD/ton exposure. Their findings are reported in this document.
Date: November 5, 1958
Creator: McCall, R. C. & Bernard, R. M.
open access

An Abrasive Cutoff Machine for Metallurgical Research on Radioactive Materials

Description: An abrasive cutoff machine design, based upon a previous model, (1) was undertaken to provide for the sampling of radioactive material. the design objective was; first, to provide samples for metallographic examination, second, to provide samples for physical and mechanical property testing, and, third, to meet the following design requirements: 1. Remote operation. 2. Airborne contamination control. 3. Radioactive waste collection. 4. Remote maintenance.
Date: January 5, 1957
Creator: Boyd, C. L.
open access

Aerodynamic and hydrodynamic characteristics of a deck-inlet multijet water-based-aircraft configuration designed for supersonic flight

Description: From Introduction: "In the present investigation, lift, drag, and pitching moment were determined over a Mach number range 0.6 to 1.42. Smooth-water takeoff and landing stability and resistance were investigated. A brief check of the rough-water spray and behavior was also made."
Date: December 5, 1956
Creator: Bielat, Ralph P.; Coffee, Claude W., Jr. & Petynia, William W.
open access

Aerodynamic and Lateral-Control Characteristics of a 1/28-Scale Model of the Bell X-1 Airplane Wing-Fuselage Combination: Transonic-Bump Method

Description: Report discussing an investigation into the lateral-control characteristics and the pitching-moment characteristics of a scale model of the X-1 wing-fuselage configuration. Information about the estimated variation of rolling effectiveness and wing-fuselage pitching-moment coefficient is described in detail.
Date: May 5, 1950
Creator: Lockwood, Vernard E.
open access

Aerodynamic Characteristics at a Mach Number of 1.25 of a 6-Percent-Thick Triangular Wing and 6- and 9-Percent-Thick Triangular Wings in Combination With a Fuselage: Wing Aspect Ratio 2.31, Biconvex Airfoil Sections

Description: Report discussing testing to determine the aerodynamic characteristics of two semispan delta-wing configurations. Information about the lift characteristics, drag characteristics, pitching-moment characteristics, and comparison with other results is provided.
Date: May 5, 1950
Creator: Hall, Albert W. & Morris, Garland J.
open access

Aerodynamic characteristics at high and low subsonic Mach numbers of four NACA 6-series airfoil sections at angles of attack from -2 to 31 degrees

Description: From Introduction: "The airfoil sections tested, which differ only in thickness ratio, were the NACA 64-006, 64-008, 64-010, and 641-012. Lift, drag, and pitching-moment data were obtained for Mach numbers of 0.3 to that for tunnel choke at angles of attack of -2^o to 31^o. The results of this investigation are reported herein."
Date: June 5, 1953
Creator: Wilson, Homer B., Jr. & Horton, Elmer A.
open access

The aerodynamic characteristics at transonic speeds of a model with a 45 degree sweptback wing, including the effect of leading edge slats and a low horizontal tail

Description: Report presenting an investigation in the 16-foot transonic tunnel to determine the effects of leading-edge slats on the aerodynamic and longitudinal stability characteristics of a model of a swept-wing fighter-type airplane. Two different spanwise extents of leading-edge slats were tested, from 35 to 95 percent semispan and from 46 to 95 percent semispan. Results regarding the lift characteristics, drag characteristics and lift-drag ratios, stability characteristics, and flow-study pictures ar… more
Date: April 5, 1954
Creator: Runckel, Jack F. & Schmeer, James W.
open access

Aerodynamic Characteristics of a 6-Percent-Thick Symmetrical Circular-Arc Airfoil Having a 30-Percent-Chord Trailing-Edge Flap at a Mach Number of 6.9

Description: Memorandum presenting an investigation of the flow characteristics over a 6-percent-thick symmetrical circular-arc airfoil section with a 30-percent-chord trailing-edge flap at a Mach number of 6.90 and a Reynolds number of 1.65 x 10(sub 6). The model was tested over an angle-of-attack range of 0 to 16 degrees and a flap-deflection range of -16 degrees to 16 degrees. Results regarding pressure results and aerodynamic characteristics are provided.
Date: June 5, 1956
Creator: Ridyard, Herbert W. & Fetterman, David E., Jr.
open access

Aerodynamic characteristics of a slender cone-cylinder body of revolution at a Mach number of 3.85

Description: "An experimental investigation of the aerodynamics of a slender cone-cylinder body of revolution was conducted at a Mach number of 3.85 for angles of attack of 0 degree to 10 degrees and a Reynolds number of 3.85x10(exp 6). Boundary-layer measurements at zero angle of attack are compared with the compressible-flow formulations for predicting laminar boundary-layer characteristics. Comparison of experimental pressure and force values with theoretical values showed relatively good agreement for s… more
Date: November 5, 1951
Creator: Jack, John R.
open access

Aerodynamic characteristics of several tip controls on a 60 degree wing at a Mach number of 1.61

Description: Report presenting an investigation at a Mach number of 1.61 to determine the control effectiveness characteristics of seven tip controls on a 60 degree delta wing. Pressure distribution measurements were made for a range of angles of attack and control deflections. Results regarding the effect of control deflection, effect of wing angle of attack, effect of hinge-line location, effect of fences, and effect of control size and location are provided.
Date: August 5, 1954
Creator: Lord, Douglas R. & Czarnecki, K. R.
open access

Aerodynamic load distribution over a 45 degree swept wing having a spoiler-slot-deflector aileron and other spoiler ailerons for Mach numbers from 0.60 to 1.03

Description: Report discussing an investigation of a 45 degree swept-back-wing-body combination with flap spoiler ailerons, deflector ailerons, and a spoiler-slot-deflector aileron. The pressures were measured from Mach numbers 0.60 to 1.03 and at various angles of attack.
Date: December 5, 1957
Creator: West, F. E., Jr.; Whitcomb, Charles F. & Schmeer, James W.
open access

Aerodynamics of Missiles Employing Wings of Very Low Aspect Ratio

Description: Memorandum presenting wind tunnel tests performed on a family of missiles. This paper summarizes some of the performance and stability and control characteristics of the missiles.
Date: March 5, 1956
Creator: Katzen, Elliott D. & Jorgensen, Leland H.
open access

Aircraft configurations developing high lift-drag ratios at high supersonic speeds

Description: From Introduction: "Range in more or less steady level flight depends directly on aerodynamic lift-drag ratio at high supersonic speeds, just as it does at lower speeds. This result follows from the classical Breguet range equation in the case of powered flight, and it may be easily deduced from the equations of motion for unpowered or gliding flight (see refs. 1 and 2)."
Date: March 5, 1956
Creator: Eggers, A. J., Jr. & Syvertson, Clarence A.
open access

Aircraft Nuclear Propulsion Project Quarterly Progress Report for Period Ending June 10, 1952

Description: This quarterly progress report details ongoing work at the Oak Ridge National Laboratory as part of the Aircraft Nuclear Propulsion Project. Topics of discussion include reactor theory and design, shielding research, materials research, appendixes with information on ongoing analytical chemical studies.
Date: August 5, 1952
Creator: Briant, R. C.; Buck, J. H.; Miller, A. J. & Cottrell, W. B.
open access

Altitude investigation of performance of turbine-propeller engine and its components

Description: From Introduction: "Results presented herein show the altitude performance of the turbine-propeller engine and its components and the applicability of the generalization method for predicting engine and component performance at altitudes other than the test altitude. Data from a brief investigation of windmilling and altitude starting characteristics of the engine also presented."
Date: October 5, 1950
Creator: Wallner, Lewis E. & Saari, Martin J.
open access

Altitude performance of annular combustor type turbojet engine with JFC-2 fuel

Description: An investigation was made comparing the performance of JFC-2 fuel and unleaded, clear gasoline in a 3000-pound-thrust turbojet engine. The JFC-2 fuel was a blend of percent diesel fuel and 25 percent aviation gasoline. Engine combustion efficiency was equal to that obtained with gasoline at rated engine speed and altitudes up to 35,000 feet, but at lower engine speeds or at higher altitudes the JFC-2 fuel gave lower combustion efficiency. No discernible difference was obtained in starting or lo… more
Date: February 5, 1952
Creator: Useller, James W.; Harp, James L., Jr. & Barson, Zelmar
open access

Altitude-Wind-Tunnel Investigation of Performance Characteristics of a J47D Prototype (RX1-1) Turbojet Engine With Variable-Area Exhaust Nozzle

Description: Performance of a J47D (RX1-1) turbojet engine equipped with afterburner, variable-area exhaust nozzle, and integrated electronic control was determined over a range of flight conditions. These data were obtained with the electronic control both operative and inoperative. For operation with scheduled exhaust nozzle area, the minimum specific fuel consumption of 1.15 pounds of fuel per hour per pound of net thrust occurred at about 7200 rpm at altitudes from 5000 to 25,000 feet at a flight Mach n… more
Date: September 5, 1951
Creator: Conrad, E. William & McAulay, John E.
open access

Analysis of a nuclear-powered ram-jet missile

Description: From Introduction: "The ram-jet missile studied in the present report is one type of shieldless which has the advantage of employing the simplest type of propulsion system."
Date: October 5, 1954
Creator: Rom, Frank E.
open access

Analysis of Lid Tank Neutron Data for Lead and Iron

Description: Abstract: An analysis of the lid tank neutron data for Pb-H2O and Fe-H2O is made. "Effective" fast neutron cross sections for the metals are obtained. This is based on the "one collision theory" of shielding. Values are 3.4 barns for Pb and 2.0 barns for Fe. These compare very well with those obtained by Albert and Welton based on other lid tank data and another method of calculation.
Date: January 5, 1951
Creator: Podgor, S.
open access

Analysis of Off-Design Performance of a 16-Stage Axial-Flow Compressor With Various Blade Modifications

Description: "The over-all performance of a 16-stage axial-flow compressor was determined with various stator-blade resettings and a reduction in solidity of the rotor blades in the last three stages. It was shown that little control over the sudden change in slope of the surge-limit line at intermediate speeds was obtained with the blade modifications attempted, except that some change in speed at which the change in slope occurred could be effected by stator-blade resettings" (p. 1).
Date: March 5, 1953
Creator: Medeiros, Arthur A.; Benser, William A. & Hatch, James E.
open access

Analysis of production test IP-120-A-94FP comparison of performance of ingot and low hydrogen dingot uranium fuel elements

Description: Twenty charges each of low hydrogen dingot fuel and standard ingot fuel elements were irradiated at DR-reactor. Distortion data from 22 tubes are analyzed in this document. The dingot fuel elements are prone to greater tube filling capacity (TFC) and greater daimeter growths at both center and ends of the fuel elements (the growths at center are larger than at ends). The difference between average warp values for the two types of fuel elements is not statistically significant, indicating that t… more
Date: November 5, 1958
Creator: Stewart, K. B.
open access

Analysis of rocket, ramjet, and turbojet engines for supersonic propulsion of long-range missiles. 3: Ramjet engine performance

Description: Report presenting ramjet engine performance data over a range of engine design variables to permit selection and evaluation of a ramjet engine configuration for a long-range supersonic missile. Results include engine thrust, drag, fuel consumption, area ratios, and weight, and are suitable for use in design studies of missiles incorporating either internally or externally mounted ramjet engines.
Date: August 5, 1954
Creator: Weber, Richard J. & Luidens, Roger W.
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