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Tentative design basis new 100 Area water plant embodying a close cooling water circuit

Description: The attached document includes a plot plan, flow diagram and delineation of basic assumptions upon which the report was developed. It summarizes the work which has been accomplished to date under RDA No. DC-6 in developing a recirculating water system to serve a new reactor. In order to proceed with the work under RDA No. DC-6 it has been necessary to make certain basic assumptions relative to the primary circuit requirements of RDA No. DC-3. These assumptions are explained in the report and ar… more
Date: November 14, 1951
Item Type: Refine your search to only Report
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Notes on Heat-Resistant Materials in Britain from Technical Mission October 13 to November 30, 1950

Description: Memorandum presenting a summary of heat-resistant materials obtained from interviews with alloy producers, jet-engine manufacturers, and research laboratories in Britain during October and November 1950. The primary subjects of interest included the properties of materials and service requirements for gas turbines, criteria used for judging and inspecting materials, and research developments of both a practical and fundamental nature in the field.
Date: May 14, 1951
Creator: Freeman, J. W. & Cross, Howard C.
Item Type: Refine your search to only Report
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Description and Investigation of a Dynamic Model of the XH-17 Two-Blade Jet Driven Helicopter

Description: Report presenting a description and results of an investigation of a model of the XH-17 two-blade, jet-powered helicopter. Tests were made with a standard configuration and with several modifications, including varying the size of blade counterweights, changing the control stiffness and chordwise bending stiffness of the blades, and varying the pylon and undercarriage damping and spring constants. Results regarding flutter testing, ground-vibration tests, and three-per-revolution rotor-blade un… more
Date: March 14, 1951
Creator: Brooks, George W. & Sylvester, Maurice A.
Item Type: Refine your search to only Report
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Wing-on and wing-off longitudinal characteristics of an airplane configuration having an thin unswept tapered wing of aspect ratio 3, as obtained from rocket-propelled models at Mach numbers from 0.8 to 1.4

Description: Report presenting flight tests at Mach numbers from 0.8 to 1.4 on three rocket-propelled general research models of airplane configurations. Two models had thin unswept tapered wings of aspect ratio 3 and hexagonal airfoil sections, two wings had different structural stiffness characteristics, and the third model had no wing. Results regarding the static and dynamic longitudinal stability, control, trim, and drag characteristics are provided.
Date: March 14, 1951
Creator: Gillis, Clarence L. & Vitale, A. James
Item Type: Refine your search to only Report
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Supersonic Tunnel Investigation by Means of Inclined-Plate Technique to Determine Performance of Several Nose Inlets Over Mach Number Range of 1.72 to 2.18

Description: Memorandum presenting a study using a suspended flat plate to continuously vary the Mach number in the 18- by 18-inch Mach number 1.91 supersonic tunnel. The technique was applied to the determination of pressure recovery and mass-flow characteristics of four supersonic nose inlets over the Mach number range produced. Results regarding the plate calibration and inlet performance are provided.
Date: February 14, 1951
Creator: Fox, Jerome L.
Item Type: Refine your search to only Report
open access

Force and pressure characteristics for a series of nose inlets at Mach numbers from 1.59 to 1.99 3: conical-spike all-external-compression inlet with supersonic cowl lip

Description: Memorandum presenting an investigation conducted in the Lewis 8- by 6-foot supersonic wind tunnel to determine the force and pressure characteristics of an all-external compression inlet with a conical spike and a supersonic cowl lip. Measurements of lift, drag, pitching moment, and internal and external pressures were made at free-stream Mach numbers of 1.59, 1.79, and 1.99 for a range of mass-flow ratios and angles of attack to 10 degrees.
Date: February 14, 1951
Creator: Weinstein, Maynard I. & Davids, Joseph
Item Type: Refine your search to only Report
open access

Preliminary Investigation of the Supersonic Flow Field Downstream of Wire-Mesh Nozzles in a Constant-Area Duct

Description: "An investigation was conducted in a 3.4- by 3.4-inch duct to determine the characteristics of the supersonic flow downstream of four wire-mesh screen nozzles with nominal design Mach numbers in the range between 1.97 and 2.58. Two types of disturbances were observed in the flow field: a fine network of interacting expansion and compression waves which were formed immediately downstream of the screens and appeared to dissipate within 25 to 40 wave intersections; and relatively strong oblique sh… more
Date: August 14, 1951
Creator: Gould, Lawrence I.
Item Type: Refine your search to only Report
open access

Effects of horizontal-tail position, area, and aspect ratio on low-speed static longitudinal stability and control characteristics of a 60 degrees triangular-wing model having various triangular-all-movable horizontal tails

Description: Report presenting a low-speed investigation in the stability tunnel to determine the static longitudinal stability and control characteristics of a 60 degree triangular-wing model with various triangular-all-movable horizontal tails. An all-movable trail of 10 percent of the wing area and aspect ratio 2.31 was investigated in 17 tail positions, including positions above, below, and to the rear of the assumed center of gravity.
Date: December 14, 1951
Creator: Jaquet, Byron M.
Item Type: Refine your search to only Report
open access

Time Histories of the Aerodynamic Loads on the Vertical and Horizontal Tail Surfaces of a Jet-Powered Bomber Airplane During Sideslip Maneuvers at Approximately 20,000 Feet

Description: Report presenting time histories of the aerodynamic loads on the vertical and horizontal tail surfaces of a jet-powered bomber airplane (B-45A) in sideslip maneuvers. Information about maximum measured rudder and fin loads, maximum total vertical-tail load, horizontal-tail-load dissymmetry, maximum elevator loads, and elevator-load dissymmetry is provided.
Date: March 14, 1951
Creator: Cooney, T. V. & McGowan, William A.
Item Type: Refine your search to only Report
open access

Note on flutter of a 60 degree delta wing encountered at low-supersonic speeds during the flight of a rocket-propelled model

Description: From Summary: "An analysis of the flight time history of a rocket-propelled model of a 60 degree delta-wing airplane configuration, fired for the purpose of obtaining zero-lift drag data, indicated wing flutter and subsequent failure at low-supersonic Mach numbers. This flutter occurred during the unpowered decelerating portion of the flight. The behavior of the model during flight is discussed and the mass and stiffness characteristics of a duplicate wing are presented."
Date: May 14, 1951
Creator: Lauten, William T., Jr. & Mitcham, Grady L.
Item Type: Refine your search to only Report
open access

Data presentation of force characteristics of several engine-strut-body configurations at Mach numbers of 1.8 and 2.0

Description: Investigation to determine lift, drag, and pitching-moment characteristics of several engine-strut-body combinations was conducted over range of angles of attack from 0 degrees to 10 degrees at Mach numbers of 1.8 and 2.0. The average Reynolds number based on body length was 28x106. Data are presented without analysis and indicate decreases in minimum drag and lift curve slope with decreasing in minimum drag and lift curve slope with decreasing strut length. Decreases in minimum drag also noted… more
Date: August 14, 1951
Creator: Madden, Robert T. & Kremzier, Emil J.
Item Type: Refine your search to only Report
open access

Basic pressure measurements on a fuselage and a 45 degrees sweptback wing-fuselage combination at transonic speeds in the slotted test section of the Langley 8-foot high-speed tunnel

Description: Report presenting the first results of pressure measurements obtained on a fuselage and a 45 degree sweptback wing-fuselage combination at transonic speeds in the slotted test section of the 8-foot high-speed tunnel. The test was part of a systematic investigation of varying amounts of sweepback on wings suitable for transonic flight. Results regarding the wing, fuselage, and fuselage with wing are provided.
Date: September 14, 1951
Creator: Loving, Donald L. & Williams, Claude V.
Item Type: Refine your search to only Report
open access

Flight Determination of the Effects of Wing Vortex Generators of the Aerodynamic Characteristics of the Douglas D-558-I Airplane

Description: Report presenting testing using a Douglas D-558-I airplane to determine the effect of wing vortex generators on some of the undesirable handling characteristics of aircraft flying at hypercritical speeds. The effects on buffeting, lateral unsteadiness, change in trim, and loss of control effectiveness were the primary objectives.
Date: August 14, 1951
Creator: Beeler, De E.; Bellman, Donald R. & Griffith, John H.
Item Type: Refine your search to only Report
open access

Heat transfer to bodies in a high-speed rarified-gas stream

Description: Report presents the results of an investigation to determine the equilibrium temperature and heat-transfer coefficients for transverse cylinders in a high-speed stream of rarefied gas measured over a range of Knudsen numbers (ratio of molecular-mean-free path to cylinder diameter) from 0.025 to 11.8 and for Mach numbers from 2.0 to 3.3. The range of free-stream Reynolds numbers was from 0.28 to 203. The models tested were 0.0010-, 0.0050-, 0.030-, 0.051-, 0.080-, and 0.126-inch -diameter cylind… more
Date: May 14, 1951
Creator: Stalder, Jackson R.; Goodwin, Glen & Creager, Marcus O.
Item Type: Refine your search to only Report
open access

A Comparison of the Spanwise Loading Calculated by Various Methods With Experimental Loadings Obtained on a 45 Degree Sweptback Wing of Aspect Ratio 8.02 at a Reynolds Number of 4.0 X 10(6)

Description: "This report compares the experimental force and moment data obtained by pressure measurements on a wing of aspect ratio 8.02, 45 degree sweptback of the quarter-chord line, taper ratio of 0.45, and NACA 63(sub 1)A012 airfoil sections with the calculated loadings obtained by the standard methods proposed by Weissinger, Falkner, and Multopp, as well as by several variations of these methods" (p. 1175).
Date: August 14, 1951
Creator: Schneider, William C.
Item Type: Refine your search to only Report
open access

A concrete shield-design

Description: It is shown that the use of Iron-Limonite shielding concrete and a steel frame structure can afford a saving of $1,351,000.00 when compared to 105 DR-H construction and material costs. C-431-B costs are not complete enough to use as basis except for the concrete materials. This study is based on actual records where possible and shows direct costs only. No allowances for transportation or tooling have been allowed in either case. An overall time saving on reactor shield construction of 30--60 d… more
Date: August 14, 1951
Creator: Jaske, R. T.
Item Type: Refine your search to only Report
open access

Vertical rod temperatures

Description: An important factor affecting the decision on the use of a seal around the VSR on ``C`` is the temperature at which the rod can be expected to reach. Also the temperature of the rod-tip affects the choice of tip moderating material. These temperatures are calculated for a given set of conditions for ``C`` pile. The results of the calculations are best seen by referring to the attached figures. The affects of emissivity and weight of rod can be estimated by comparing the proper curves. The assum… more
Date: August 14, 1951
Creator: Roy, G. M.
Item Type: Refine your search to only Report
open access

Short Time Corrosion Tests of Bronze, Mild Steel, T-304 Stainless Steel and 2S Aluminum in 10% Potassium Tetraborate Solution

Description: Report summarizing corrosion tests meant to determine the corrosion rates of bronze, mild steel, T-304 stainless steel and 2S aluminum in 10% potassium tetraborate solution. Tests were completed under the boiling point of each solution except for 2S aluminum, which was tested at 40C, the approximate temperature in a pile.
Date: December 14, 1951
Creator: Katayama, Y. B.
Item Type: Refine your search to only Report
open access

THE USE OF CHELATING AGENTS FOR ACCELERATING EXCRETION OF RADIOELEMENTS

Description: Although the deleterious effects of exposure to ionizing radiation were first recognized and described over fifty years ago, the adequate treatment of these effects still remains a therapeutic challenge. At the present time, when increasing numbers of our population are being exposed to radiation because of the great increase in availability and use of radioactive isotopes and because of the potential exposure of much greater numbers of people to radiation following a possible atomic bomb burst… more
Date: June 14, 1951
Creator: Foreman, Harry & Hamilton, Joseph G.
Item Type: Refine your search to only Report
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