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The Scattering of Thermal Radiation Into Open Underground Shelters

Description: From Introduction: "The elimination of the burn hazard in shelters depends upon a separate, systematic investigation of each suspected agent. The purpose of the present investigation was to evaluate the contribution made by radiant energy and, if such contribution proved to be significant, to suggest means of eliminating this component."
Date: May 1959
Creator: Davis, T. P.; Miller, N. D.; Ely, T. S.; Basso, J. A. & Pearse, H. E.
Partner: UNT Libraries Government Documents Department
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Health Protection in Beryllium Facilities Summary of Ten Years of Experience

Description: From Introduction: "The purpose of this report is to summarize the information gathered during the design and operation of these facilities so that it may be used in providing for the safe handling of beryllium materials."
Date: May 1, 1958
Creator: Breslin, A. J. & Harris, W. B.
Partner: UNT Libraries Government Documents Department
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Strontium Program: Quarterly Summary Report, May 29, 1959

Description: From Abstract: "This report is one of a sequence of quarterly reports, each designed to up-date its predecessor beginning with HASL-42, "Environmental Contamination from Weapon Tests". Herein are presented data which have accrued since HASL-55. Levels of strontinum-90 in fallout, milk, air, water, vegetation, foods, and bone are given, based on data available from February 1, 1959 to May 20, 1959."
Date: May 29, 1959
Creator: Hardy, Edward P., Jr. & Klein, Stanley
Partner: UNT Libraries Government Documents Department
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The Fabrication of Certain Jacketed Uranium Helices

Description: Report describing the fabrication of Doppler Helices, which were 1/8 inch diameter x 12 foot long uranium core completely enclosed within a thin metal jacket and wound into a spring or helix shape.
Date: May 1957
Creator: Yaggee, F. L.
Partner: UNT Libraries Government Documents Department
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Hazard Summary Report Experimental Breeder Reactor II (EBR-II)

Description: From Forward: "This report describes the present conceptions of the Experimental Breeder Reactor-II as well as the safety procedures and precautions which are currently anticipated for its operation."
Date: May 1957
Creator: Koch, L. J.; Monson, H. O.; Okrent, D.; Levenson, M.; Simmons, W. R.; Humphreys, J. R. et al.
Partner: UNT Libraries Government Documents Department
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Calculations on U235 Fission Product Decay Chains

Description: Report of equations for calculating decay of U235. The introduction states" Calculations have been made on the U235 fission product decay schemes. The results for a typical example, that of a reactor operating at 1000 kilowatts for 180 days, have been tabulated and graphed. General formulae have been used so that the results can be applied for any power level and any time of irradiation" (p. 2).
Date: May 1952
Creator: Faller, I. L.; Chapman, T. S. & West, J. M.
Partner: UNT Libraries Government Documents Department
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Performance at Mach Numbers 3.07, 1.89, and 0 of Inlets Designed for Inlet-Engine Matching Up to Mach 3

Description: Report presenting performance of a two-dimensional external-compression inlet designed for various methods of inlet-engine matching up to Mach 3 at Mach 1.89 and Mach 0. Results regarding shock geometry, two-shock ramps, isentropic ramps, profiles, and cowl drag for the various Mach number tests are provided.
Date: May 20, 1958
Creator: Gertsma, L. W. & Beheim, M. A.
Partner: UNT Libraries Government Documents Department
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Performance of Isentropic Nose Inlets at Mach Number of 5.6

Description: Memorandum presenting an investigation of the performance of inlet configurations with a forebody designed for isentropic external compression at a nominal Mach number of 5.6. At zero angle of attack, all the configurations yielded larger total-pressure recoveries than had previously been obtained with a single-conical-shock inlet. Results regarding the flow about the forebody, inlet performance, and performance comparisons are provided.
Date: May 6, 1954
Creator: Bernstein, Harry & Haefeli, Rudolph C.
Partner: UNT Libraries Government Documents Department
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Effects of Modifications to a Control Surface on a 6-Percent-Thick Unswept Wing on the Transonic Control-Surface Flutter Derivatives

Description: Transonic flutter derivatives for unswept wing control surface configurations determined by pressure cell measurements. The control surfaces were mounted on a wing with an aspect ratio of 3, a taper ratio of 0.6, and a wing-thickness ratio of 0.06. Results regarding aerodynamic balance, vortex generators, splitter-plate configurations, and wedges are provided.
Date: May 2, 1958
Creator: Wyss, John A.; Sorenson, Robert M. & Gambucci, Bruno J.
Partner: UNT Libraries Government Documents Department
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Some Effects of Flow Spoilers and of Aerodynamic Balance on the Oscillating Hinge Moments for a Swept Fin-Rudder Combination in a Transonic Wind Tunnel

Description: Memorandum presenting force-oscillation tests made in the 8-foot transonic pressure tunnel to investigate some effects of an overhang-type aerodynamic balance and of a flow spoiler on the dynamic hinge-moment characteristics of a full-span flap-type rudder on a 5-percent-thick, swept vertical fin of low aspect ratio. Test results how that the aerodynamic damping moment on the plain rudder becomes unstable near a Mach number of 0.975 and remains unstable to the maximum speed of the tests.
Date: May 28, 1958
Creator: Herr, Robert W.; Gibson, Frederick W. & Osborne, Robert S.
Partner: UNT Libraries Government Documents Department
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Relation of Currently Estimated ANP Performance to Required ANP Performance

Description: Memorandum presenting an investigation of performance estimates of aircraft nuclear propulsion (ANP) systems. This paper includes a relation of current estimated ANP performance to the future requirements that nuclear propulsion systems will be required to meet.
Date: May 16, 1957
Creator: Rothrock, Addison M. & Cesaro, Richard S.
Partner: UNT Libraries Government Documents Department
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The Effect of Blunt-Trailing-Edge Modifications on the High-Speed Stability and Control Characteristics of a Swept-Wing Fighter Airplane

Description: An investigation was conducted on a 35 deg swept-wing fighter airplane to determine the effects of several blunt-trailing-edge modifications to the wing and tail on the high-speed stability and control characteristics and tracking performance. The results indicated significant improvement in the pitch-up characteristics for the blunt-aileron configuration at Mach numbers around 0.90. As a result of increased effectiveness of the blunt-trailing-edge aileron, the roll-off, customarily experienced with the unmodified airplane in wings-level flight between Mach numbers of about 0.9 and 1.0 was eliminated, The results also indicated that the increased effectiveness of the blunt aileron more than offset the large associated aileron hinge moment, resulting in significant improvement in the rolling performance at Mach numbers between 0.85 and 1.0. It appeared from these results that the tracking performance with the blunt-aileron configuration in the pitch-up and buffeting flight region at high Mach numbers was considerably improved over that of the unmodified airplane; however, the tracking errors of 8 to 15 mils were definitely unsatisfactory. A drag increment of about O.OOl5 due to the blunt ailerons was noted at Mach numbers to about 0.85. The drag increment was 0 at Mach numbers above 0.90.
Date: May 26, 1954
Creator: Sadoff, Melvin; Matteson, Frederick H. & Van Dyke, Rudolph D., Jr.
Partner: UNT Libraries Government Documents Department
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Low-Pressure Performance of a Tubular Combustor With Gaseous Hydrogen

Description: 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.
Partner: UNT Libraries Government Documents Department
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A Feasibility Study of the Flare-Cylinder Configuration as a Reentry Body Shape for an Intermediate Range Ballistic Missile

Description: "A study has been made of a flare-cylinder configuration to investigate its feasibility as a reentry body of an intermediate range ballistic missile. Factors considered were heating, weight, stability, and impact velocity. A series of trajectories covering the possible range of weight-drag ratios were computed for simple truncated nose shapes of varying pointedness, and hence varying weight-drag ratios" (p. 1).
Date: May 28, 1958
Creator: Hall, James R. & Garland, Benjamine J.
Partner: UNT Libraries Government Documents Department
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A Summary of Results Obtained During Flight Simulation of Several Aircraft Prototypes With Variable-Stability Airplanes

Description: Memorandum describing an investigation using two airplanes, an F6F-3 and F-86A, each fitted with servo equipment for varying in flight the lateral and directional stability and handling characteristics, which have been flown by test pilots to simulate the predicted dynamic behavior of six prototype airplanes. The methods of simulation and the types and ranges of variables considered are presented and the results of the individual programs are discussed.
Date: May 25, 1956
Creator: McNeill, Walter E. & Creer, Brent Y.
Partner: UNT Libraries Government Documents Department
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High-Altitude Performance of J71-A-11 Turbojet Engine and Its Components Using JP-4 and Gaseous-Hydrogen Fuels

Description: Report presenting data to determine the component and overall engine performance up to an altitude limit for the J71-A-11 (600-B36) turbojet engine. Engine operation using JP-4 fuel at Mach number 0.8 was satisfactory up to an altitude of about 60,000 to 65,000 feet, and engine operation with marginal combustion stability was maintained to an altitude of about 80,000 feet. Results regarding the altitude operating limits, component performance, overall engine performance, contribution of individual component losses to overall engine performance losses, exhaust-nozzle-area requirements, and altitude performance at rated engine conditions are provided.
Date: May 29, 1957
Creator: Smith, Ivan D. & Saari, Martin J.
Partner: UNT Libraries Government Documents Department
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Induction System Characteristics and Engine Surge Occurrence for Two Fighter-Type Airplanes

Description: Memorandum presenting an investigation conducted to measure and compare the total-pressure recovery and distortion characteristics at the compressor face of two single-place fighter-type airplanes with similar two-spool turbojet engines, but with dissimilar inlets. The total-pressure recovery was relatively independent of angle of attack and mass-flow ratio for both airplanes except for a significant decrease in pressure recovery with angle of attack for airplane B at the highest Mach numbers tested.
Date: May 26, 1958
Creator: Larson, Terry J.; Thomas, George M. & Bellman, Donald R.
Partner: UNT Libraries Government Documents Department
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Fabrication and Properties of Hot-Pressed Molybdenum Disilicide

Description: Report presenting an investigation of hot-pressed molbdenum disilicide bodies produced by industrial processes at a temperature of 2950 degrees and a pressure of 3000 pounds per square inch. Results regarding the short-time tensile strength, stress-rupture data, compression strength, air-corrosion resistance, hardness, coefficient of linear thermal expansion, thermal conductivity, and density are provided.
Date: May 26, 1950
Creator: Long, Roger A.
Partner: UNT Libraries Government Documents Department
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Analysis of a Pneumatic Probe for Measuring Exhaust-Gas Temperatures with Some Preliminary Experimental Results

Description: "A pneumatic probe based on continuity of mass flow through two restrictions separated by a cooling chamber was constructed to measure gas temperature at and beyond the limit of thermocouples. This probe consisted of a subsonic flat-plate orifice for the first restriction and a sonic-flow converging-diverging nozzle for the second restriction. The effect of variation in gas constants on the calibration is examined for common engine-exhaust gases" (p. 1).
Date: May 21, 1952
Creator: Scadron, Marvin D.
Partner: UNT Libraries Government Documents Department
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Longitudinal Aerodynamic Characteristics of Various Configurations of a Revised 1/22-Scale Model of the Republic F-105 Airplane at Mach Numbers of 1.41 and 2.01

Description: Report presenting an investigation of a model of the Republic F-105 airplane to determine the static longitudinal aerodynamic characteristics of a revised configuration. The revisions included a lengthened fuselage, a relocated canopy, a contoured fuselage afterbody, a ventral fin, and an enlarged vertical tail. Results regarding the effect of stores, effect of dive-brake flaps, effect of forebody modifications, gun blisters, and duct air bleed, and a comparison of the modified model with the original are provided.
Date: May 4, 1956
Creator: Foster, Gerald V.
Partner: UNT Libraries Government Documents Department
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Altitude Performance of a Turbojet Engine Using Pentaborane Fuel

Description: Memorandum presenting a turbojet engine with a two-stage turbine operated with pentaborane fuel continuously for 11.5 minutes at a simulated altitude of 55,000 feet at a flight Mach number of 0.8. The engine incorporated an NACA combustor designed specifically for use with pentaborane fuel. Results regarding oxide formation and deposition, engine operating point, effect of oxide deposits on component performance, effect of oxide deposition on overall performance, and some operational comments are provided.
Date: May 20, 1957
Creator: Sivo, Joseph N.
Partner: UNT Libraries Government Documents Department
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A Comparison of Flight-Measured Carrier- Approach Speeds With Values Predicted by Several Different Criteria for 41 Fighter-Type Airplane Configurations

Description: Memorandum presenting lift and drag characteristics that have been determined in flight in the landing-approach configuration on 41 jet-propelled fighter-type airplane arrangements, including various wing boundary-layer-control installations. Minimum comfortable approach speeds for carrier-type landings were evaluated for these airplanes by four test pilots. Results regarding the presentation of data, methods for the prediction of minimum comfortable approach speed, reasons for limiting approach speed, comparison of flight and predicted approach speeds, and comparison of test pilots' and service pilots' approach speed are provided.
Date: May 8, 1958
Creator: White, Maurice D.; Schlaff, Bernard A. & Drinkwater, Fred J., III
Partner: UNT Libraries Government Documents Department
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Investigation of Lithium Hydride and Magnesium as High-Temperature Internal Coolants With Several Skin Materials

Description: Memorandum presenting an investigation of hemispherical nose shapes of titanium, stainless steel coated with aluminum oxide, and uncoated stainless steel with lithium hydride and magnesium as internal coolants. Results regarding titanium models, stainless-steel models (uncoated), stainless-steel models coated with aluminum oxide, solution effects on the decomposition temperature of lithium hydride, effect of lithium hydride and magnesium on temperature measurements, and efficiency of models cooled with lithium hydride are provided.
Date: May 28, 1958
Creator: Modisette, Jerry L.
Partner: UNT Libraries Government Documents Department
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