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9-Zoom : A One-Dimensional, Multigroup, Neutron Diffusion Theory Reactor Code for the IBM 709

Description: The following document describes the usage and purpose of the neutron diffusion theory reactor program 9-Zoom, a memory-contained program that takes advantage of 709 features such as, for example, preferential order of multiply by zero, and for small problems approaches input-output limitations with excellent convergence properties.
Date: August 25, 1959
Creator: Stone, S. P.; Collins, E. T. & Lenihan, S. R.
Partner: UNT Libraries Government Documents Department
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Additional measurements of the low-speed static stability of a configuration employing three triangular wing panels and a body of equal length

Description: From Introduction: "The results of an investigation of the low-speed static stability of a simplified model of such an arrangement having one of the airfoils placed vertically on top of the body and the other two as wing panels having negative dihedral are presented in reference 1. In order to provide information for predicting the effects of changes in the basic configuration on the low-speed stability characteristics presented in reference 1, additional measurements have been made."
Date: July 25, 1955
Creator: Delany, Noel K.
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics at Supersonic Speeds of a Series of Wing-Body Combinations Having Cambered Wings With an Aspect Ratio of 3.5 and a Taper Ratio of 0.2: Effect at M = 2.01 of Nacelle Shape and Position on the Aerodynamic Characteristics in Pitch of Two Wing-Body Combinations with 47 Degree Sweptback Wings

Description: Memorandum presenting an investigation at M = 2.01 in the 4- by 4-foot supersonic pressure tunnel to determine the effect of a series of nacelles on the longitudinal stability characteristics of a sweptback wing-body combination. Nacelle shape and position were varied on a configuration with a 6-percent-thick wing with an aspect ratio of 3.5, a taper ratio of 0.2, and 47 degrees of sweep at the quarter chord.
Date: July 25, 1952
Creator: Driver, Cornelius
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics at Transonic Speeds of a Tapered 45 Degree Sweptback Wing of Aspect Ratio 3 Having a Full-Span Flap Type of Control With Overhang Balance: Transonic-Bump Method

Description: From Introduction: "This paper presents the aerodynamic characteristics of low-aspect-ratio sweptback wing having a full-span flap type of control employing an overhanging balance of 50 percent of the flap chord.The main purpose of this investigation was to determine if overhang balances are an effective means of reducing the hinge moments of flap type of controls at transonic speeds."
Date: January 25, 1952
Creator: Lockwood, Vernard E. & Hagerman, John R.
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics of a 60 degree delta wing having a half-delta tip control at a Mach number of 4.04

Description: From Introduction: "Numerous tests of tip controls on delta wings at transonic and low supersonic speeds have shown that such configurations provide satisfactory rolling-moment effectiveness, and that the hinge can be controlled by proper location of the hinge line (ref. 1). The purpose of the present tests is to determine the characteristics of such a configuration at Mach number of 4.04 and a Reynolds number of 5.8 X 10^6, based on the wing mean aerodynamic chord."
Date: April 25, 1955
Creator: Ulmann, Edward F. & Smith, Fred M.
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of Missile Configurations With Wings of Low Aspect Ratio for Various Combinations of Forebodies, Afterbodies, and Nose Shapes for Combined Angles of Attack and Sideslip at a Mach Number of 2.01

Description: "An investigation has been made in the Langley 4-by-4-foot supersonic pressure tunnel to determine the aerodynamic characteristics of a series of missile configurations having low-aspect-ratio wings at a Mach number of 2.01. The effects of wing plan form and size, length-diameter ratio, forebody and afterbody length, boattailed and flared afterbodies, and component force and moment data are presented for combined angles of attack and sideslip to about 28 degrees. No analysis of the data was made in this report" (p. 1).
Date: June 25, 1957
Creator: Robinson, Ross B.
Partner: UNT Libraries Government Documents Department
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Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) 4: aerodynamic characteristics of series of four bodies having near-parabolic noses and cylindrical afterbodies

Description: Pressure distributions and forces for a series of four bodies of revolution having nose-fineness ratios varying from 4 to 10 have been obtained and compared with theory for a Mach number of 3.12, a Reynolds number range of 2x10(sup)6 to 14x10(sup)6, and angles of attack from zero to 9 degrees. In general, a comparison of the experimental data with a second-order theory showed good agreement for the range of variables investigated.
Date: January 25, 1954
Creator: Jack, John R. & Moskowitz, Barry
Partner: UNT Libraries Government Documents Department
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The Ames supersonic free-flight wind tunnel

Description: From Introduction: "Because of the unusual nature of this equipment, and because it is proving to be very useful for certain kinds of aerodynamic research, this report has been prepared. It contains a description of the equipment and its use to obtain aerodynamic coefficients. The imperfections in the wind-tunnel air stream and their effect on model tests are also discussed."
Date: April 25, 1952
Creator: Seiff, Alvin; James, Carlton S.; Canning, Thomas N. & Boissevain, Alfred G.
Partner: UNT Libraries Government Documents Department
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The Ames Supersonic Free-Flight Wind Tunnel

Description: Memorandum presenting a description of the Ames supersonic free-flight wind tunnel, which is a new piece of equipment for aerodynamic research at high supersonic Mach numbers. It has a wide Mach number range extending from low supersonic speeds to Mach numbers in excess of 10. The air stream in the tunnel is imperfect, mainly due to a symmetrical pair of oblique shock waves which reflect down the test section.
Date: April 25, 1952
Creator: Seiff, Alvin; James, Carlton S.; Canning, Thomas N. & Boissevain, Alfred G.
Partner: UNT Libraries Government Documents Department
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Analysis of cooling-air requirements of corrugated-insert-type turbine blades suitable for a supersonic turbojet engine

Description: From Introduction: "This report presents the cooling-air requirements of a "paper" air-cooled turbojet engine operating over a wide range of flight Mach numbers and altitudes. The results are presented for a two-stage-turbine turbo-jet engine having a turbine-inlet temperature of 2500^o R and operating at sea-level static conditions and flight Mach numbers from 0.90 to 2.5 and flight altitudes from 40,000 to 70,000 feet. In addition, the effect of decreasing the blade-inlet cooling-air temperature on the required coolant-flow ratio is presented."
Date: April 25, 1956
Creator: Ziemer, Robert R. & Slone, Henry O.
Partner: UNT Libraries Government Documents Department
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Analysis of Factors Affecting Selection and Design of Air-Cooled Single-Stage Turbine for Turbojet Engines 1: Turbine Performance and Engine Weight-Flow Capacity

Description: Memorandum presenting an analysis to determine the compressor pressure ratios and specific weight flows obtainable with single-stage air-cooled turbines for both nonafterburning and afterburning turbojet engines operating at a flight Mach number of 2 in the stratosphere. Wide ranges in turbine-inlet temperature, tip speed, hub-tip radius ratio, and coolant-flow ratio were considered.
Date: May 25, 1954
Creator: Rossbach, Richard J.; Schramm, Wilson B. & Hubbartt, James E.
Partner: UNT Libraries Government Documents Department
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ANALYSIS OF NEUTRON PULSES IN A GODIVA-TYPE REACTOR

Description: Some calculations have been made to estimate the characteristics of a neutron-burst type fast reactor similar to Godiva but made up of relatively small component parts--the so-called "layered assembly." One spherical and three cylindrical assemblies have been considered. Critical masses, assuming 5% voids, range from 58 to 65 kg of 93.4% enriched U/sup 235/. For a reactivity addition of 0.33 dollars above prompt criticals bursts between 2 x 10/sup 17/ and 6.7 x 10/ sup 17/ fissions were computed with accompanying temperature rises varying from 514 to 1600 deg C. The burst width at half-maximum was about 12 microseconds. To obtain an idea of the possibilities of stress reduction which might be achieved by layerings an assembly made of small rings was considered. While the critical masses obtained here are believed to be fairly accurates the predictions concerning mechanical energy generated, total fissions, and burst width may be subject to sizeable error due to the many simplitications required to allow hand computations. Neverthelesss considerable improvement in safety and burst-size is indicated by the use of a "layered assembly" instead of an assembly composed of relatively thick parts. (auth)
Date: February 25, 1959
Creator: Nestor, C.W. & Tobias, M.
Partner: UNT Libraries Government Documents Department
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Analysis of V-G records from ten types of Navy airplanes in squadron operations during the period 1949 to 1953

Description: From Introduction: "The purpose of this paper is to present an analysis of the data for the remaining airplanes where the data were sufficient to warrant analysis. The data analyzed represent totals of 351 to 5660 hours of operations with ten types of Navy airplanes and were recorded during the period 1949 to 1953."
Date: March 25, 1955
Creator: Mayer, John P. & Harris, Agnes E.
Partner: UNT Libraries Government Documents Department
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Analytic evaluation of effect of inlet-air temperature and combustion pressure on combustion performance of boron slurries and blends of pentaborane in octene-1 : Supplement I - Influence of new boric-oxide vapor-pressure data on calculated performanc

Description: "The theoretical performance of pentaborane has been recalculated using recent data on the vapor pressure of boric oxide. Previous calculations were based upon vapor-pressure data obtained some years ago by a method not as accurate as that employed in current investigations. The recalculated performance data for pentaborane differ appreciably from previously published data and are considered more accurate for evaluation of the relative potentialities of boron-containing fuels" (p. 1).
Date: May 25, 1956
Creator: Tower, Leonard K.
Partner: UNT Libraries Government Documents Department
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Analytical determination of effect of turbine cooling-air-impeller performance on engine performance and comparison of experimentally determined performance of impellers with and without inducer vanes

Description: Report presenting an analytical and experimental investigation of the effects of cooling-air impeller performance on turbojet-engine performance at 70 and 100 percent of rated engine speed. Analysis indicated that the impeller performance has little effect on engine performance at rated engine speed for the coolant flows considered. Results regarding the impeller total-pressure ratio and cooling air available with compressor bleed are provided.
Date: October 25, 1954
Creator: Schafer, Louis J., Jr. & Hickel, Robert O.
Partner: UNT Libraries Government Documents Department
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Analytical investigation of factors affecting the performance of single-stage turbines having rotor-tip discharge of cooling air

Description: From Introduction: "The purpose of this report is to further analyze the turbine performance results of reference 1 with the objective of isolating the contribution of the cooling air to the turbine performance and establishing some systematic relation between these cooling-air effects and the turbine operational parameters."
Date: April 25, 1956
Creator: Smith, Gordon T. & Hickel, Robert O.
Partner: UNT Libraries Government Documents Department
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Analytical procedures for the plutonium Metal Fabrication Process

Description: Report describing the results of the cupferron extraction-copper spark method in determining the impurity elements in plutonium metal. This was required the 234-5 Project analytical program.
Date: July 25, 1952
Creator: Bierlein, T. K.; Kendall, L. F. & Van Tuyl, H. H.
Partner: UNT Libraries Government Documents Department
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Analytical Procedures for the Plutonium Metal Fabrication Process

Description: Report describing methods of determining trace impurities in plutonium in connection with the Metal Fabrication Process. The methods included are the cupferron extraction-copper spark method and the direct copper spark method.
Date: July 25, 1952
Creator: Bierlein, T. K.; Kendall, L. F. & Van Tuyl, H. H.
Partner: UNT Libraries Government Documents Department
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Applications of auxiliary air injectors to supersonic wind tunnels

Description: Report presenting a discussion of the adverse effects of high compression ratio requirements for supersonic wind tunnels as well as the use of second throats for alleviating those effects. The results indicated that an auxiliary air-injector system can reduce starting and running compression ratios as compared to a conventional wind tunnel with a divergent diffuser.
Date: November 25, 1953
Creator: Spiegel, Joseph M.; Hofstetter, Robert U. & Kuehn, Donald M.
Partner: UNT Libraries Government Documents Department
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Aqueous Homogeneous Reactors for Producing Central-Station Power

Description: Report issued by the Oak Ridge National Laboratory discussing aqueous homogeneous reactors used in central-station power. As stated in the introduction, "it contains an evaluation of the potentiality of producing power only, as exhibited by aqueous homogeneous systems" (p. 6). This report includes tables, and illustrations.
Date: May 25, 1951
Creator: Briggs, R. B.; Haubenreich, P. N.; Sanders, J. P.; Aven, R. E.; Zapp, F. C.; Segaser, C. L. et al.
Partner: UNT Libraries Government Documents Department
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Arc Calcination of Thorium Oxide

Description: An over-all description of the background material on the use of electrical arcs for heating of powders is presented as well as a summary of experimental studies on the arc calcination of thoria. Favorable results have been indicated both with heating thoria powder in an arc heated gas and with thoria formed into a consumable electrode. Use of a consumable electrode produces thoria particles 0.1 to 0.01 mu in diameter. It is recommended that additional electrodes be fabricated and further arc calcination tests be run to produce a quantity of product sufficient for evaluation. (auth)
Date: June 25, 1958
Creator: Johnsson, K.O.
Partner: UNT Libraries Government Documents Department
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Army Gas-Cooled Reactor Systems Program Monthly Progress Report: April 1959

Description: Abstract: This monthly progress report covers the activities of the Army Gas-Cooled Reactor System Program for April 1959. The program includes a water-moderated heterogeneous reactor (Gas-Cooled Reactor Experiment I), a graphite-moderated homogeneous reactor (Gas-Cooled Reactor Experiment II), a mobile gas-cooled reactor (ML-1), and the coordination of the Gas Turbine Test Facility. [It reports] the progress of each project, the associated tests and data evaluation, the applicable design criteria, and the fabrication of reactor components" (p. 1).
Date: May 25, 1959
Creator: Aerojet-General Corporation
Partner: UNT Libraries Government Documents Department
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Army Gas-Cooled Reactor Systems Program. Monthly Progress Report for April 1959

Description: The Army Gas Cooled Reactor System Program includes water moderated heterogeneous reactor (Gas Cooled Reactor Experiment I), a graphite moderated homogeneous reactor (Gas Cooled Reactor Experiment II), a mobile gas cooled reactor (ML-1), and the co ordination of thc Gas Turbine Test Facility. The progress of each project, the associated tests and data evaluation, the applicabie design criteria, and the fabrication of reactor components are briefly summarized. (For preceding period see IDO-28538.) (W.D.M.)
Date: May 25, 1959
Partner: UNT Libraries Government Documents Department
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