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SRE CONTROL ROD SHIELDING REQUIREMENTS

Description: Data taken on radiation traverse of the Mark 1 control rod were analyzed. Future radiation levels for all SRE control and safety rods were predicted from this. The shielding necessary to ship a complete rod and that necessary to protect a person doing maintenance work on these rods were calculated. The unshielded gamma dose rate 1 cm from the surface of the most highly activated portion of the control rod was calculated to be 5.0 x 10/sup 4/ r/hr 14 days after shutdown following an extended power run of 90 days duration. (M.C.G.)
Date: October 22, 1957
Creator: Whittum, H.O.
Partner: UNT Libraries Government Documents Department
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Special filter samples of Hanford process effluent gases

Description: This document contains information on special filter samples of Hanford Process Effluent Gases. The filters are identified by code numbers only. Included in this paper are tables explaining the sample code numbers, sampling locations, and process conditions during sampling. Also included, is a copy of the monthly and quarterly average results for Regional Monitoring's routine stack program for the fourth quarter of 1956.
Date: January 22, 1957
Creator: Soldat, J.K.
Partner: UNT Libraries Government Documents Department
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Aileron and Elevator Hinge Moments of the Bell X-1 Airplane Measured in Transonic Flight

Description: "During the flight investigation of the X-1 airplane the hinge moments of the elevator and aileron control surfaces have been measured over a Mach number range extending to above 1.0. The results of these measurements are presented in this paper" (p. 2).
Date: June 22, 1953
Creator: Drake, Hubert M. & McKay, John B.
Partner: UNT Libraries Government Documents Department
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An analysis of the tracking performances of two straight-wing and two swept-wing fighter airplanes with fixed sights in a standardized test maneuver

Description: From Introduction: "This report presents the initial study, the tracking performance of typical fighter airplanes with fixed gunsights. The types of airplanes tested afford two comparisons of particular interest: that between typical World War II and currently operational fighters of greatly increased speed and altitude, and that between conventional and irreversabile power-boosted controls with artificial feel, both installed on the same airframe."
Date: October 22, 1953
Creator: Rathert, George A., Jr.; Gadeberg, Burnett L. & Ziff, Howard L.
Partner: UNT Libraries Government Documents Department
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Preliminary investigation of the effects of body contouring as specified by the transonic area rule on the aerodynamic characteristics of a delta wing-body combination at Mach numbers of 1.41 and 2.01

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effects of body contouring as specified by the transonic drag-rise area rule on the aerodynamic characteristics of a delta wing-body combination at Mach numbers of 1.41 and 2.01. Body contouring reduced zero-lift drag of a delta wing-body combination from that of a basic wing-body combination without contouring by 18 percent at Mach number 1.41 and 6 percent at Mach number 2.01. Results regarding the characteristics at zero lift and characteristics for the lifting condition are provided.
Date: September 22, 1953
Creator: Carlson, Harry W.
Partner: UNT Libraries Government Documents Department
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Some Effects of Spanwise Aileron Location and Wing Structural Rigidity on the Rolling Effectiveness of 0.3-Chord Flap-Type Ailerons on a Tapered Wing Having 63 Degrees Sweepback at the Leading Edge and Naca 64A005 Airfoil Sections

Description: Report presenting an investigation of some effects of aileron spanwise location and wing structural rigidity on the rolling power of 0.3-chord plain, flap-type ailerons on a wing with a taper ratio of 0.25, an aspect ratio of 3.5, and swept back 63 degrees at the leading edge. Results regarding the aeroelastic effects and aileron span and spanwise location are provided.
Date: June 22, 1951
Creator: Strass, H. Kurt; Fields, E. M. & Schult, Eugene D.
Partner: UNT Libraries Government Documents Department
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Investigation of the Effects of Variations in the Reynolds Number Between 0.4 X 10(Exp 6) 3.0 X 10(Exp 6) on the Low-Speed Aerodynamic Characteristics of Three Low-Aspect-Ratio Symmetrical Wings With Rectangular Plan Forms

Description: Report presenting an investigation of the effect of Reynolds number and the addition of leading-edge roughness on the aerodynamic characteristics of wings with aspect ratio 1, 2, and 3, a rectangular plan form, square-cut wing tips, and NACA 0012 airfoil sections. Results regarding lift and moment, lift-curve slope, and maximum lift are provided.
Date: September 22, 1952
Creator: Jones, George W., Jr.
Partner: UNT Libraries Government Documents Department
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Preliminary air-flow and thrust calibrations of several conical Cooling-air ejectors with a primary to secondary temperature ratio of 1.0 I :diameter ratios of 1.21 and 1.10

Description: Report presenting an investigation of the performance of several conical cooling-air ejectors at primary jet pressure ratios from 1 to 10, secondary shroud pressure ratios from 0.60 to 4.00, and primary to secondary temperature ratio of 1.0. The investigation centered on primary air flow, secondary air flow, primary nozzle thrust, and gross ejector thrust.
Date: July 22, 1952
Creator: Greathouse, W. K. & Hollister, D. P.
Partner: UNT Libraries Government Documents Department
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Effects of three types of blunt trailing edges on the aerodynamic characteristics of a plane tapered wing of aspect ratio 3.1, with a 3-percent- thick biconvex section

Description: Report presenting effects of wing trailing-edge bluntness on aerodynamic characteristics of a wing-body combination at a range of Mach numbers and Reynolds numbers. Modifications were made to the rear half of a basic plane tapered wing of aspect ratio 3.1 and a 3-percent-thick, circular-arc, biconvex section with three types of trailing-edge shapes. Results regarding the lift characteristics, pitching-moment characteristics, drag characteristics, and maximum lift-drag ratio are provided.
Date: July 22, 1952
Creator: Dugan, Duane W.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of a Shielded Total-Pressure Tube at Transonic Speeds

Description: Report presenting testing of a shielded total-pressure tube with a curved venturi entry in order to obtain the variation of total-pressure error with angle of attack from a range of 0 to 60 degrees and for a range of Mach numbers. The critical angle was found to vary from about 57 degrees at Mach number 0.90 to 56 degrees at Mach number 1.10.
Date: January 22, 1952
Creator: Gracey, William; Pearson, Albin O. & Russell, Walter R.
Partner: UNT Libraries Government Documents Department
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Effects of Auxiliary and Ejector Pumping on the Mach Number Attainable in a 4 1/2- by 4 1/2-Inch Slotted Tunnel at Low Pressure Ratios

Description: Report presenting the results of an investigation to determine the pressure ratios required to operate a slotted tunnel through a range of Mach numbers where the speed variation is affected by removal of air from the main stream by auxiliary pumping, use of a main-stream-operated ejector located downstream of the test section, and a combination of these methods. Testing was conducted in order to improve the accuracy of transonic wind-tunnel testing.
Date: January 22, 1954
Creator: Dennard, John S. & Little, Barney H., Jr.
Partner: UNT Libraries Government Documents Department
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Flight Determination of Drag of Normal-Shock Nose Inlets With Various Cowling Profiles at Mach Numbers From 0.9 to 1.5

Description: Report discussing free-flight tests of normal-shock nose-inlet models with 1-series, parabolic, and conic cowling profiles in order to investigate the external drag characteristics at an angle of attack of 0 degrees. The testing occurred at a variety of Mach numbers, mass-flow ratios, and Reynolds numbers. Information about the effect of afterbody length, basic data, and effect of cowl shape is provided.
Date: October 22, 1953
Creator: Sears, R. I.; Merlet, C. F. & Putland, L. W.
Partner: UNT Libraries Government Documents Department
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The Synthesis of Butylsilanes by a Large-Scale Reduction with Lithium Aluminum Hydride

Description: "Eighty pounds of butylsilanes required for test purposes was synthesized by reducing butyltrichlorosilane with lithium aluminum hydride in dioxane solution. This was safely and successfully accomplished by operating in steel equipment under an atmosphere of oil-pumped nitrogen to minimize the hazards involved in conducting this operation on a large scale. The apparatus and procedure used to carry out the necessary manipulations are described in this report" (p. 1).
Date: July 22, 1953
Creator: Kaye, Samuel; Tannenbaum, Stanley & Hipsher, Harold F.
Partner: UNT Libraries Government Documents Department
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A Transonic Wind-Tunnel Investigation of the Effect of Modifications to an Indented Body in Combination With a 45 Degree Sweptback Wing

Description: Memorandum presenting an investigation of modifications to an indented body which was originally designed on the basis of the transonic drag-rise rule to determine the effects on the aerodynamic characteristics of a 45 degree sweptback-wing-body combination. The investigation covered a range of Mach numbers and angles of attack. Results regarding lift, drag for the nonlifting case, drag for the lifting case, maximum lift-to-drag ratios, and pitching moment are provided.
Date: September 22, 1953
Creator: Loving, Donald L.
Partner: UNT Libraries Government Documents Department
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The effect of initial rate of subsonic diffusion on the stable subcritical mass-flow range of a conical shock diffuser

Description: Report presenting results of a systematic study in the 8- by 6-foot supersonic wind tunnel to determine the effect that area distribution in the subsonic diffuser might have on stability and overall performance of conical-type supersonic diffusers. Drag, pressure recovery, and mass flow are presented for five diffusers designed for maximum mass flow at Mach number 2.0.
Date: July 22, 1953
Creator: Nettles, J. C.
Partner: UNT Libraries Government Documents Department
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A study of the use of controls and the resulting airplane response during service training operations of four jet fighter airplanes

Description: Report presenting results from a limited flight program to obtain information on airplane response and actual rates and amounts of control motion used by service pilot in performance of squadron operational training. Results regarding control deflection, control rates, airplane angular velocities, airplane angular accelerations, angle of attack and angle of sideslip, airplane load factors, and airspeed and altitude are provided.
Date: June 22, 1954
Creator: Mayer, John P.; Hamer, Harold A. & Huss, Carl R.
Partner: UNT Libraries Government Documents Department
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High-altitude performance of 9.5-inch-diameter tubular experimental combustor with fuel staging

Description: Report presenting an investigation of 57 experimental tubular designs embodying adjacent fuel-rich and air-rich regions and axial staging of the fuel introduction at simulated high-altitude conditions. Results regarding the development of pilot, development of secondary-air admission sleeve, development of final configuration, and performance of best configuration are provided.
Date: March 22, 1954
Creator: Scull, Wilfred E.
Partner: UNT Libraries Government Documents Department
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Flight and Preflight Evaluation of an Automatic Thrust-Coefficient Control System in a Twin-Engine Ram-Jet Missile

Description: Report presenting a flight and preflight evaluation of an automatic thrust-coefficient control system in a twin-engine ram-jet missile. A flicker-type single-loop servocontrol system is shown to be a usable way of controlling ram-jet thrust coefficients.
Date: January 22, 1954
Creator: Dettwyler, H. Rudolph & Trout, Otto F., Jr.
Partner: UNT Libraries Government Documents Department
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Calculated Effect of Uranium Distribution on Reflector Control Effectiveness for a Water-Moderated Power Reactor

Description: Report presenting two-group theory calculations to determine the effect of nonuniform uranium loading as compared to uniform loading on the reflector control effectiveness attainable in a large thermal reactor usable for aircraft power application. Results regarding reactivities and investments, uranium distributions, and power distributions are provided.
Date: January 22, 1954
Creator: Fox, Thomas A. & Valerino, Michael F.
Partner: UNT Libraries Government Documents Department
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Performance characteristics of aircraft cooling ejectors having short cylindrical shrouds

Description: The factors affecting the performance of ejector suitable for aircraft cooling are investigated theoretically and experimentally. The investigation covers a range of shroud-to-nozzle diameter ratios from 1.1 to 1.6, of shroud lengths from 0.2 to 2.28 nozzle diameters, of secondary-to-primary weight-flow ratios from 0 to 0.12, and of ambient-to-nozzle pressure ratios from 0.7 to 0.06. The results of a simplified theoretical analysis based on each type of flow are in good agreement with those experimentally obtained.
Date: May 22, 1951
Creator: Kochendorfer, Fred D. & Rousso, Morris D.
Partner: UNT Libraries Government Documents Department
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Investigation of mechanisms of blade failure of forged Hastelloy B and cast Stellite 21 turbine blades in turbojet engine

Description: An investigation was conducted to study the mechanisms of blade failure of forged Hastelloy B and cast Stellite 21. The blades were mounted in a 16-25-6 alloy rotor and subjected to 20-minute cycles consisting of 15 minutes at rated speed and approximately 5 minutes at idle. The first failures of the Hastelloy B and Stellite 21 blades were probably the result of excessive vibratory stresses and occurred after 14.25 and 16.75 hours, respectively. After 28.75 hours of operation, all but 3 of the original 25 Hastelloy B blades had either failed or contained stress-rupture-type cracks and four of the original 27 Stellite 21 blades contained stress-rupture-type cracks.
Date: August 22, 1951
Creator: Yaker, C.; Robards, C. F. & Garrett, F. B.
Partner: UNT Libraries Government Documents Department
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Pressure Distributions on the Blade Sections of the NACA 10-(3)(090)-03 Propeller Under Operating Conditions

Description: The third report in a series of five that present unanalyzed pressure data obtained in tests of five full-scale propellers with NACA 16-series blade sections. Pressure distributions on the blade sections were measured under operating conditions to determine the aerodynamic characteristics of each blade section. This particular report presents information for nine radial stations of the NACA 10-(3)(090)-03 propeller.
Date: March 22, 1950
Creator: Johnson, Peter J.
Partner: UNT Libraries Government Documents Department
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Wind-tunnel tests of a 0.16-scale model of the X-3 airplane at high subsonic speeds: wing and fuselage pressure distribution

Description: Report presenting measurements of wing and fuselage pressure distributions made at low and high subsonic Mach numbers on a scale model of the projected X-3 research airplane. Tests were conducted in pitch and yaw and included measurements of the total pressure in the fuselage boundary layer at the location of the left boundary-layer bleed scoop.
Date: June 22, 1950
Creator: Cleary, Joseph W. & Mellenthin, Jack A.
Partner: UNT Libraries Government Documents Department
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An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: Force Characteristics of the Complete Configuration and Its Various Components at Mach Numbers of 1.40 and 1.59

Description: Report presenting an investigation of a supersonic aircraft configuration and various combinations of its components at a range of Mach numbers. Longitudinal- and lateral-force characteristics of the configurations, as well as longitudinal- and lateral-stability derivatives, are provided.
Date: January 22, 1951
Creator: Smith, Norman F. & Marte, Jack E.
Partner: UNT Libraries Government Documents Department
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