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Large-scale low-speed wind-tunnel tests of a model having a 60 degree delta horizontal canard control surface and wing to obtain static-longitudinal-stability and canard surface hinge-moment data

Description: Report presenting a wind-tunnel investigation of a model equipped with a 60 degree delta wing and a 60 degree delta horizontal all-movable canard control surface to determine the stability, control, and canard-surface hinge-moment characteristics at low speeds and at a Reynolds number of 9 x 10(exp 6). Two longitudinal positions of the canard surface were tested. Results regarding lift and pitching moment, drag, and hinge moment are provided.
Date: June 17, 1954
Creator: Burrows, Dale L.
Partner: UNT Libraries Government Documents Department
open access

Removal of cesium from uranium recovery process wastes

Description: The Uranium Recovery Process (TBP Process) at Hanford extracts and decontaminates uranium from the Metal Waste produced in the Bismuth Phosphate Process. Aqueous waste, approximately equal in volume to that of the Metal Waste itself, results from the process. Although of several years' age, these wastes are still sufficiently radioactive that they must be returned to underground tanks for storage. For several years aqueous wastes of low radioactive content have been discharged to ground at Hanf… more
Date: May 17, 1954
Creator: Burns, R. E.; Brandt, R. L. & Clifford, W. E.
Partner: UNT Libraries Government Documents Department
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Uranium blending

Description: No Description Available.
Date: May 17, 1954
Creator: Smith, A. E.
Partner: UNT Libraries Government Documents Department
open access

Summary of Recent External Neutron-Yield Measurements by the MnSO₄ Tank Method

Description: Report that summarizes unreported neutron-yield data for the MnSO₄ tank method. Other yield measurements had been reported in other quarterly reports prior to the completion of this one.
Date: September 17, 1954
Creator: Crandall, Walter E. & Millburn, George P.
Partner: UNT Libraries Government Documents Department
open access

Final reports on PT 105-551-A and Supplement A, ``High exposure thorium`` and PT 105-516-A, ``Effects of irradiation of thorium slugs``

Description: This report discusses Production Test 105-516-A which was written to determine the stability by both measurement and visual examination, of thorium slugs as used in flattening columns to exposures in excess of 400 MWD/AT. Both rolled and extruded thorium slugs were used; the highest exposures reached were about 1000 MWD/AT. Also discussed is Production Test 105-551-A which was written to demonstrate the stability of thorium slugs as used in flattening columns at exposures up to approximately 15… more
Date: November 17, 1954
Creator: Brugge, R. O.
Partner: UNT Libraries Government Documents Department
open access

Hanford Atomic Products Operation monthly report, August 1954

Description: This document presents a summary of work and progress at the Hanford Engineer Works for August 1954. The report is divided into sections by department. A plant wide general summary is included at the beginning of the report, after which the departmental summaries begin. The Manufacturing Department report plant statistics, and summaries for the Metal Preparation, Reactor and Separation sections. The Engineering Department`s section summarizes work for the Technical, Design, and Project Sections… more
Date: September 17, 1954
Partner: UNT Libraries Government Documents Department
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Activity of Ru 103 and Ru 106 in pile fission products

Description: The purpose of this document is to provide a means for estimating the age of ruthenium ground contamination when the ration of Ru 103 activity to Ru 106 activity in the contamination is known.
Date: August 17, 1954
Creator: Gumprecht, R. O.
Partner: UNT Libraries Government Documents Department
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Investigation at Supersonic Speeds of the Effect of Jet Mach Number and Divergence Angle of the Nozzle Upon the Pressure of the Base Annulus of a Body of Revolution

Description: Report presenting an investigation in the 9-inch supersonic tunnel to determine the jet effects for varying jet Mach number and nozzle divergence angle upon the pressure on the base annulus of a model with a cylindrical afterbody. Testing occurred over a wide range of jet static pressure ratios and Mach numbers. Results regarding sonic jets and supersonic jets are provided.
Date: December 17, 1954
Creator: Bromm, August F., Jr. & O'Donnell, Robert M.
Partner: UNT Libraries Government Documents Department
open access

The effect of stick-force gradient and stick gearing on the tracking accuracy of a fighter airplane

Description: Report presenting steady straight-and-level and steady turning tracking runs against an aerial target using an F-51H airplane equipped with a fixed optical sight and with various combinations of maneuvering stick-force and stick-deflection gradients. Results regarding aim wander, elevator movement, and stick-force variation for various test conditions are provided.
Date: December 17, 1954
Creator: Abramovitz, Marvin & Van Dyke, Rudolph D., Jr.
Partner: UNT Libraries Government Documents Department
open access

Analysis of Turbulent Heat Transfer, Mass Transfer, and Friction in Smooth Tubes at High Prandtl and Schmidt Numbers

Description: From Introduction: "In the analysis given herein, which was made at the NACA Lewis laboratory, the expression for eddy diffusivity given in reference 1 is modified in order to account for the effect of kinematic viscosity in reducing the turbulence in the region close to the wall. The effects of variable viscosity and of length-to-diameter ratio are also investigated."
Date: February 17, 1954
Creator: Deissler, Robert G.
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Effects of Jet Exhaust and Reynolds Number Upon the Flow Over the Vertical Stabilizer and Rudder of the Douglas D-558-II Research Airplane at Mach Numbers of 1.62, 1.93, and 2.41

Description: Memorandum presenting an investigation to determine the effects of jet exhaust and Reynolds number on the flow over the vertical stabilizer and rudder of the Douglas D-558-II research airplane with special attention to an understanding of the rudder reversals experienced in flight on the full-scale airplane. Tests were made at Mach numbers of 1.62, 1.93, and 2.41 over a range of ratios of jet static pressure to stream static pressure from the jet-off ratio to about 40 and for a maximum range of… more
Date: June 17, 1954
Creator: Grigsby, Carl E.
Partner: UNT Libraries Government Documents Department
open access

Effect of ground interference on the aerodynamic and flow characteristics of a 42 degree sweptback wing at Reynolds numbers up to 6.8 x 10(6)

Description: Report presents the results of an investigation of the effects of ground interference on the aerodynamic characteristics of a 42 degree sweptback wing at distances 0.68 and 0.92 of the mean aerodynamic chord from the simulated ground to the 0.25-chord point of the mean aerodynamic chord. Survey data behind the wing, both with and without the simulated ground, are presented in the form of contour charts of downwash, sidewash, and dynamic-pressure ratio at longitudinal stations of 2.0 and 2.8 mea… more
Date: December 17, 1954
Creator: Furlong, G. Chester & Bollech, Thomas V.
Partner: UNT Libraries Government Documents Department
open access

Thrust and pumping characteristics of a series of ejector-type exhaust nozzles at subsonic and supersonic flight speeds

Description: Report presenting an investigation conducted in the 8- by 6-foot supersonic wind tunnel to determine the thrust and pumping characteristics of a series of ejector exhaust nozzles. Data were obtained for various ejector diameter and spacing ratios at a range of Mach numbers, pressure-ratio ranges, and secondary-primary weight-flow ratios. Results regarding the primary-nozzle mass-flow coefficients, performance comparison of configurations, effect of free-stream Mach number on the ejectors, net t… more
Date: November 17, 1954
Creator: Hearth, Donald P. & Valerino, Alfred S.
Partner: UNT Libraries Government Documents Department
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Thrust and Pumping Characteristics of a Series of Ejector-type Exhaust Nozzles at Subsonic and Supersonic Flight Speeds

Description: Report presenting an investigation in the supersonic wind tunnel to determine the thrust and pumping characteristics of a series of ejector exhaust nozzles. Results indicated that the free-stream Mach number had no effect on those characteristics of the ejectors in the range for which the secondary flow was choked.
Date: November 17, 1954
Creator: Hearth, Donald P. & Valerino, Alfred S.
Partner: UNT Libraries Government Documents Department
open access

Effects of Molecular Weight on Crazing and Tensile Properties of Polymethyl Methacrylate

Description: Memorandum reporting the tensile and crazing properties for five cast polymethy lmethacrylate sheets in which the molecular weight of the resin was 90,000, 120,000, 200,000, 490,000, and 3,160,000. Both stress crazing and stress-solvent crazing tests were conducted. Results regarding the standard tensile tests, stress-solvent crazing tests, and discussion of failure and crazing are provided.
Date: February 17, 1954
Creator: Wolock, I.; Sherman, M. A. & Axilrod, B. M.
Partner: UNT Libraries Government Documents Department
open access

Determination of Longitudinal Stability in Supersonic Accelerated Maneuvers for the Douglas D-558-II Research Airplane

Description: Report discussing testing of a Douglas D-558-II to investigate its longitudinal stability characteristics in accelerated flight at supersonic speeds. Information about the normal-force coefficients and their relation to stability and pitch-up of the aircraft is included.
Date: February 17, 1954
Creator: Ankenbruck, Herman O.
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of the Aerodynamic Derivatives and Performance of Control Systems of Two Full-Scale Guided Bombs

Description: Report presenting the aerodynamic stability derivatives and pitch and yaw control effectiveness of two full-scale guided bombs over a range of Mach numbers in free-flight drop tests. Results regarding performance information, roll control operation, and aerodynamic characteristics are provided.
Date: June 17, 1954
Creator: Seaberg, Ernest C. & Geller, Edward S.
Partner: UNT Libraries Government Documents Department
open access

Summary of some rocket-model investigations of effects of wing aspect ratio and thickness on aileron rolling effectiveness including some effects of spanwise aileron location for sweptback wings with aspect ratio of 8

Description: Report presenting the rolling effectiveness of 0.2-chord, trailing-edge ailerons on high-aspect-ratio sweptback wings over a range of Mach numbers. Some effects of spanwise aileron location on rolling effectiveness were measured by testing ailerons on the inboard half, the outboard half, and the full length of the exposed wings.
Date: February 17, 1954
Creator: Strass, H. Kurt
Partner: UNT Libraries Government Documents Department
open access

Altitude-wind-tunnel investigation of several afterburner configurations having moderately high burner-inlet velocities

Description: From Introduction: "The screech investigation, reported in reference 1, included a large number of afterburner configurations. Several of these configurations are presented herein to show the effects of afterburner-inlet gas whirl pattern, flame-holder design, and fuel distribution on performance as determined by combustion efficiency, augmented thrust ratio, and special fuel consumption."
Date: November 17, 1954
Creator: Schulze, F. W.; Bloomer, H. E. & Miller, R. R.
Partner: UNT Libraries Government Documents Department
open access

Effects of rigid spoilers on the two-dimensional flutter derivatives of airfoils oscillating in pitch at high subsonic speeds

Description: Report presenting a study of the effects of spoilers with fixed heights equal to 2.5 to 4 percent of the airfoil chord on the aerodynamic lift and moment flutter derivatives of oscillating two-dimensional airfoils. Results regarding the typical effects of spoiler deflection, effects of Mach number, and aerodynamic torsional instability boundaries for fixed spoiler heights as affected by airfoil profile are provided.
Date: December 17, 1954
Creator: Monfort, James C. & Wyss, John A.
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Hydrodynamic Characteristics of a 1/10-Size Powered Dynamic Model of the Martin M-267 Patrol-Type Seaplane with Two Forebody Configurations: TED No. NACA DE 376

Description: Report presenting an investigation of the hydrodynamic characteristics of a scale powered dynamic model of a patrol-type seaplane designed by the Glenn L. Martin Company. The seaplane had a high-aspect-ratio wing and a T-tail with an all-movable stabilizer. A comparison was made between two forebody configurations, one with a sharp forebody keel in cross section and the other with the forebody cross section rounded in the vicinity of the keel.
Date: August 17, 1954
Creator: Mottard, Elmo J. & Coffee, Claude W., Jr.
Partner: UNT Libraries Government Documents Department
open access

Drag and Heat Transfer on a Parabolic Body of Revolution (NACA RM-10) in Free Flight to Mach Number 2 With Both Constant and Varying Reynolds Number and Heating Effects on Turbulent Skin Friction

Description: Report discussing testing on a research model to obtain experimental drag and heat-transfer data under constant and varying conditions of Reynolds number and heating effects. Average body turbulent skin-friction-drag coefficients were determined for both constant and varying heating effect.
Date: June 17, 1954
Creator: Maloney, Joseph P.
Partner: UNT Libraries Government Documents Department
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