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Safety system for RDA-DC-3

Description: The basis for the safety control system for RDA-DC-3 is set forth in HDC-2462 with revisions as noted here. These conditions are satisfied by an array of safety control components comprising 37 vertical safety rods and 51 ball hoppers (51 total vertical graphite slots) as shown on drawing H-1-21403.
Date: February 18, 1952
Creator: Reed, E. L.; Robinson, T. F. & Roy, G. M.
Partner: UNT Libraries Government Documents Department
open access

Hanford Works Monthly Report: March 1952

Description: This is a progress report of the production reactors on the Hanford Reservation for the month of April 1952. This report takes each division (e.g., manufacturing, medical, accounting, occupational safety, security, reactor operations, etc.) of the site and summarizes its accomplishments and employee relations for that month.
Date: April 18, 1952
Creator: Prout, G. R.
Partner: UNT Libraries Government Documents Department
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HIGH TEMPERATURE TESTS OF STANDARD NEEDLE BEARINGS

Description: S>Standard needle bearinge were tested dry and with NaK lubrication at 800 deg F with an oscillating motion up to 5 deg and found satisfactory. (T. R.H.)
Date: December 18, 1952
Creator: Bedford, A.W. Jr. & Vail, D.B.
Partner: UNT Libraries Government Documents Department
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DESIGN DATA FOR ISHR (SECOND EDITION)

Description: No Description Available.
Date: November 18, 1952
Creator: Zapp, F C & Haubenreich, P N
Partner: UNT Libraries Government Documents Department
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Boundary-Layer Measurements on Several Porous Materials With Suction Applied

Description: Memorandum presenting the boundary-layer velocity profiles were measured on ten samples of various porous materials and on impervious aluminum plate mounted flush with the inner surface of the side wall of a small wind tunnel. Suction was applied to the back side of the porous test materials through a 4-inch-square opening. Results regarding measurements on the impervious plate and measurements on porous materials without suction and with suction are provided.
Date: June 18, 1952
Creator: McCullough, George B. & Gambucci, Bruno J.
Partner: UNT Libraries Government Documents Department
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Control effectiveness and hinge-moment characteristics at low-speed of large-chord, horn-balanced, flap-type controls on a triangular wing of aspect ratio 2

Description: Report presenting an investigation of large-chord flap-type controls with sweptback hinge lines and with various sizes and shapes of horn balances on a triangular wing of aspect ratio 2. Changes in the following elements were investigated: shielding of the horn balance, percentage of horn balance, trailing-edge thickness, flap nose seal, contour of the horn balance, and Reynolds number.
Date: August 18, 1952
Creator: Dods, Jules B., Jr.
Partner: UNT Libraries Government Documents Department
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Transonic aerodynamic characteristics of three thin triangular wings and a trapezoidal wing, all of low aspect ratio

Description: Report presenting an investigation in the high-speed wind tunnel to determine the aerodynamic characteristics of three triangular wings and a trapezoidal wing through the transonic speed range by use of the bump technique. Data was obtained over a range of Mach and Reynolds numbers. Results regarding the lift, drag, pitching moment, and lift-drag ratio of the various wings are provided.
Date: July 18, 1952
Creator: Emerson, Horace F. & Gale, Bernard M.
Partner: UNT Libraries Government Documents Department
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Two-dimensional chord-wise load distributions at transonic speeds

Description: Report presenting testing on the NACA 16-009 airfoil and on eight airfoils of the NACA 6A series, which shows that the chordwise loading due to lift at a Mach number of 1.0 is insignificantly affected by thickness distribution within the range of airfoil shapes presented and only slightly affected by thickness. Results regarding the experimental loading on symmetrical airfoils, method of estimating pressure distribution, experimental loadings on cambered airfoils, and scope of method are provid… more
Date: February 18, 1952
Creator: Lindsey, Walter F. & Dick, Richard S.
Partner: UNT Libraries Government Documents Department
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The Forces and Pressure Distribution at Subsonic Speeds on a Cambered and Twisted Wing Having 45 Degrees of Sweepback and Aspect Ratio of 3 and a Taper Ratio of 0.5

Description: Memorandum presenting an investigation conducted to determine the effects of scale and compressibility on the forces, moments, and pressure distribution on a cambered and twisted wing with an aspect ratio of 3.0 and a taper ratio of 0.5. Lift, drag, and pitching-moment data and the chordwise distribution of static pressure at seven spanwise stations are presented for specified Mach and Reynolds numbers. In order to determine the effects of camber and twist, the force, moment, and pressure data … more
Date: July 18, 1952
Creator: Boltz, Frederick W. & Kolbe, Carl D.
Partner: UNT Libraries Government Documents Department
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Analytical procedures for rapid selection of coolant passage configurations for air-cooled turbine rotor blades and for evaluation of heat-transfer, strength, and pressure-loss characteristics

Description: Report presenting a method based on geometric factors of the coolant passage was evolved for the rapid selection and evaluation of coolant passage configurations for air-cooled turbine rotor blades. The most promising coolant passage configurations are analyzed to obtain absolute values of the required cooling-air weight flow, pressure loss, and strength characteristics.
Date: September 18, 1952
Creator: Ziemer, Robert R. & Slone, Henry O.
Partner: UNT Libraries Government Documents Department
open access

Preliminary Survey of Boundary-Layer Development at a Nominal Mach Number of 5.5

Description: Memorandum presenting a measurement of the mean skin-friction coefficients on a flat-plate model, with and without initial roughness, and on a wind tunnel wall were measured at a nominal Mach number of 5.5 over a range of Reynolds numbers.
Date: June 18, 1952
Creator: Bloom, Harold L.
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics extended to high angles of attack at transonic speeds of a small-scale 0 degree sweep wing, 45 degree sweptback wing, and 60 degree delta wing

Description: Report presenting an investigation of a series of wings of various plan forms in the high-velocity field of the side-wall reflection plate of the 7- by 10-foot tunnel at a range of angles of attack and Mach numbers. The results indicated that the maximum lift coefficients obtainable increased with increase in sweep angle and decreased with Mach number at the lower subsonic Mach numbers.
Date: November 18, 1952
Creator: Wiley, Harleth G.
Partner: UNT Libraries Government Documents Department
open access

Investigation of losses in the XJ35-A-23 two-stage turbine

Description: Report presenting an investigation of the stage work distribution and losses through the turbine at design conditions of the XJ35-A-23 two-stage turbine. The investigation showed that the poor performance was primarily due to large whirl velocities at the turbine exit, choking in the second-stage rotor, and a choking condition upstream of the physical blade throat. If these conditions are eliminated, satisfactory two-stage turbine performance can be obtained.
Date: August 18, 1952
Creator: Rebeske, John J., Jr. & Forrette, Robert E.
Partner: UNT Libraries Government Documents Department
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Preliminary investigation of the drag characteristics of the NACA RM-10 missile at Mach numbers of 1.40 and 1.59 in the Langley 4- by 4-foot tunnel

Description: Report presenting testing of a parabolic body of revolution in the 4- by 4-foot supersonic tunnel at two Mach numbers. The investigation included the effects of Reynolds number, fins, internal contour of body base, and two support systems on body pressure and force drag at an angle of attack of 0 degrees.
Date: April 18, 1952
Creator: Hasel, Lowell E.; Sinclair, Archibald R. & Hamilton, Clyde V.
Partner: UNT Libraries Government Documents Department
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Cold-air investigation of a turbine with nontwisted rotor blades suitable for air cooling

Description: Report presenting the performance characteristics of a turbine with nontwisted rotor blades suitable for air cooling. Results regarding overall performance and flow surveys at the stator and rotor exits are provided.
Date: March 18, 1952
Creator: Heaton, Thomas R.; Slivka, William R. & Westra, Leonard F.
Partner: UNT Libraries Government Documents Department
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Longitudinal Frequency-Response and Stability Characteristics of the Douglas D-558-II Airplane as Determined From Transient Response to a Mach Number of 0.96

Description: Report presenting the longitudinal frequency-response characteristics and the stability derivatives of the Douglas D-558-II airplane at a range of Mach numbers and altitudes. Results of experimentation were compared to computed values.
Date: September 18, 1952
Creator: Holleman, Euclid C.
Partner: UNT Libraries Government Documents Department
open access

A small-scale investigation of the effect of spanwise and chordwise positioning of an ogive-cylinder underwing nacelle on the high-speed aerodynamic characteristics of a 45 degree sweptback tapered-in-thickness wing of aspect ratio 6

Description: Report presenting an investigation of a nacelle in three chordwise locations at each of four spanwise locations in an underwing position on a small-size semi-span model of a wing sweptback 45 degrees and tapered in thickness from 9 percent at the root to 3 percent at the tip. Results regarding drag characteristics, lift-drag ratios, lift characteristics, pitching moment characteristics, and lateral center of pressure are provided.
Date: December 18, 1952
Creator: Silvers, H. Norman & King, Thomas J., Jr.
Partner: UNT Libraries Government Documents Department
open access

Some Dynamic Characteristics of a Turbojet Engine for Large Accelerations

Description: Memorandum presenting a review of the acceleration characteristics of an axial-flow turbojet engine with a fixed-area exhaust nozzle as obtained from transients induced by large steps in fuel flow under sea-level static conditions. Maximum acceleration and thrust appeared obtainable through the use of a proposed fuel schedule that required only small initial steps in fuel flow. Results regarding linearity, maximum acceleration and thrust, and fuel-flow schedule are provided.
Date: August 18, 1952
Creator: Heppler, Herbert; Novik, David & Dandois, Marcel
Partner: UNT Libraries Government Documents Department
open access

Performance of Supersonic Scoop Inlets

Description: A brief summary is made of the performance of a series of variable-geometry type scoop inlets investigated at the Lewis Laboratory on a model of the X-3 airplane fuselage. Data are presented for a range of inlet mass-flow ratios over a Mach number range from 0 to 2 and from 0 degrees to 12 degrees angle of attack. Rounded-lip inlets are found to give satisfactory performance to a Mach number of 1.5. Use of sharp rather than blunt lip configurations is shown to provide considerable gains in avai… more
Date: February 18, 1952
Creator: Weinstein, M. I.
Partner: UNT Libraries Government Documents Department
open access

Characteristics of flap-type spoiler ailerons at various locations on a 60 degree delta wing with a double slotted flap

Description: Report presenting a low-speed wind-tunnel investigation to determine the static lateral control characteristics of flap-type spoiler ailerons on a thin delta wing equipped with a double slotted flap. A spoiler located on the flap gave rolling-moment coefficients that varied fairly linearly with spoiler projects and with about the same magnitude for either the flap-retracted or flap-deflected position.
Date: December 18, 1952
Creator: Croom, Delwin R.
Partner: UNT Libraries Government Documents Department
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