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Aerodynamic Characteristics of Tapered Wings Having Aspect Ratios of 4, 6, and 8, Quarter-Chord Lines Swept Back 45 Degrees, and NACA 63(Sub 1)a012 Airfoil Sections: Transonic-Bump Method

Description: Report presenting testing of a series of three wings over a range of Mach numbers by the use of the transonic-bump technique. The lift, drag, pitching-moment, and root-bending-moment data of wings of a variety of aspect ratios but with the same quarter-chord lines and airfoil sections were obtained.
Date: June 13, 1951
Creator: Polhamus, Edward C. & King, Thomas J., Jr.
Partner: UNT Libraries Government Documents Department
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Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) 1: body of revolution with near-parabolic forebody and cylindrical afterbody

Description: An experimental investigation of the aerodynamic characteristics of a slender, square-based body of revolution was conducted at a Mach number of 3.12 for angles of attack from 0 degree to 10 degrees and for Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6). Boundary-layer measurements at zero angle of attack are compared with several compressible flow formulating for predicting boundary-layer characteristics. Comparison of experimental pressure and force values with theoretical values showe… more
Date: November 13, 1951
Creator: Jack, John R. & Burgess, Warren C.
Partner: UNT Libraries Government Documents Department
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An analysis of the suitability of various coring patterns for inclusion in ``C`` Reactor

Description: Preliminary meetings on coring of the graphite have been held with interested parties of the Technical and Production Divisions at which time the advantages and problems of coring were discussed. The advantages and the problems which must be surmounted in order to core have been presented to the working committee. A study of the means of accomplishing coring has been made considering only the central and maximum fringe coring. It is important that the minimum and maximum coring be established a… more
Date: April 13, 1951
Creator: Roy, G. M. & Andersen, R. K.
Partner: UNT Libraries Government Documents Department
open access

Calculated effects of turbine rotor-blade cooling-air flow, altitude, and compressor bleed point on performance of a turbojet engine

Description: Effects of air-cooling turbine rotor blades on performance of a turbojet engine were calculated for a range of altitudes from sea level to 40,000 feet and a range of coolant flows up to 3 percent of compressor air flow, for two conditions of coolant bleed from the compressor. Bleeding at required coolant pressure resulted in a sea-level thrust reduction approximately twice the percentage coolant flow and in an increase in specific fuel consumption approximately equal to percentage coolant flow.… more
Date: August 13, 1951
Creator: Arne, Vernon L. & Nachtigall, Alfred J.
Partner: UNT Libraries Government Documents Department
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Comparison of Purex Process Results in Mixer Settlers and Pulse Columns

Description: The feasibility study of the Purex flowsheet in pulse column equipment has been completed in the ORNL Purex Pilot Plant. Eleven runs have been made in the pilot plant at a throughput of 75 kg to 125 kg of uranium per day.
Date: August 13, 1951
Creator: Darby, D. O.
Partner: UNT Libraries Government Documents Department
open access

The Determination of Hydrogen in Magnesium, Lithium, and Magnesium Alloys

Description: The following report describes the process of the determination of hydrogen in magnesium, lithium, and magnesium alloys, including methods of analyzing magnesium-lithium alloys for hydrogen, and the tin-fusion method used for determining the hydrogen content of pure magnesium that can also be used to analyze pure lithium for hydrogen.
Date: November 13, 1951
Creator: Mallett, Manley William, 1909-; Gerds, A. F. & Griffith, C. B.
Partner: UNT Libraries Government Documents Department
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Effect of Section Thickness and Trailing-Edge Radius on the Performance of NACA 65-Series Compressor Blades in Cascade at Low Speeds

Description: Report presenting tests of NACA 65-series compressor blades cambered to an isolated airfoil lift coefficient of 1.2 at several maximum section thicknesses to obtain the effect of maximum section thickness on section operating characteristics. Information about surface pressure trends, design angle-of-attack selection, drag, operating range, and critical Mach number is also provided. Changing the section thickness was not found to significantly affect the design angle of attack selected.
Date: December 13, 1951
Creator: Herrig, L. Joseph; Emery, James C. & Erwin, John R.
Partner: UNT Libraries Government Documents Department
open access

Effectiveness of Thermal-Pneumatic Airfoil-Ice-Protection System

Description: From Summary: "Icing and drag investigations were conducted in the NACA Lewis icing research tunnel employing a combination thermal-pneumatic de-icer mounted on a 42-inch-chord NACA 0018 airfoil. The de-icer consisted of a 3-inch-wide electrically heated strip symmetrically located about the leading edge with inflatable tubes on the upper and lower airfoil surfaces aft of the heated area. The entire de-icer extended to approximately 25 percent of chord. A maximum power density of 9.25 watts per… more
Date: April 13, 1951
Creator: Gowan, William H., Jr. & Mulholland, Donald R.
Partner: UNT Libraries Government Documents Department
open access

The Evaluation of Definite Integrals, and a Quasi-Monte-Carlo Method Based on the Properties of Algebraic Numbers

Description: A formula is given for the approximate evaluation of multiple definite integrals using the ergodic property of a certain transformation of the unit cube into itself. Estimates of the rate of convergence are made for sufficiently smooth integrand. The work was motivated by a belief, that appeared at one time justified, that a substantial improvement of the accuracy of Monte Carlo method would result from use of the principles described herein. Although that belief proved groundless in numerical … more
Date: October 13, 1951
Creator: Richtmyer, R. D.
Partner: UNT Libraries Government Documents Department
open access

Experimental Rolling of Uranium : Lackawanna No. 3

Description: The following report is one of a series of rolling tests to establish the rolling process for Feed Materials Production Center at Fernold, Ohio. The primary objective of this program is to find a mechanically feasible process for continuous rolling of uranium.
Date: December 13, 1951
Creator: Riches, J. W.
Partner: UNT Libraries Government Documents Department
open access

Force and pressure characteristics for a series of nose inlets at Mach numbers from 1.59 to 1.99 5: analysis and comparison on basis of ram-jet aircraft range and operational characteristics

Description: Performance of four experimentally investigated axially symmetric spike-type nose inlets is compared on basis of ram-jet-engine aircraft range and operational problems. At design conditions, calculated peak engine efficiencies varied 25 percent from the highest value which indicates importance of inlet design. Calculations for a typical supersonic aircraft indicate possible increase in range if engine is flown at moderate angle of attack and result in engine lift utilized. For engines with fixe… more
Date: September 13, 1951
Creator: Howard, E.; Luidens, R. W. & Allen, J. L.
Partner: UNT Libraries Government Documents Department
open access

GAS COOLING OF A POROUS HEAT SOURCE

Description: No Description Available.
Date: December 13, 1951
Creator: Green, L. Jr.
Partner: UNT Libraries Government Documents Department
open access

The Hydrolysis of Tributyl Phosphate Ad Its Effect on the Purex Process

Description: From abstract: "The rate of hydrolysis of TBP and the effect of the hydrolysis products in the Purex Process have been studied. Hydrolytic conditions may be encountered in the process which would lead to formation of dibutyl phosphoric acid, causing significant losses of tetravalent plutonium in stripping. This situation may be easily alleviated by reducing and stripping the plutonium in the trivalent state."
Date: December 13, 1951
Creator: Reilly, V. J. & Lanham, W. B.
Partner: UNT Libraries Government Documents Department
open access

IV. Production and Heating

Description: Calculations are developed which indicate the Pu production is an infinite lattice
Date: February 13, 1951
Creator: Brown, Harold
Partner: UNT Libraries Government Documents Department
open access

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : plane triangular wing of aspect ratio 3 with NACA 0003-63 section

Description: Report presenting a wing-body combination with a plane triangular wing of aspect ratio 3 and NACA 0003-63 sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date: September 13, 1951
Creator: Heitmeyer, John C.
Partner: UNT Libraries Government Documents Department
open access

Low-Speed Characteristics of a 45 Degree Swept Wing with Leading-Edge Inlets

Description: Memorandum presenting an investigation to determine the low-speed aerodynamic characteristics of a 45 degree swept wing with leading-edge inlets. The wing had a constant chord and completely spanned the wind tunnel. Results regarding surface-pressure characteristics, lift and pitching-moment characteristics, wake-drag characteristics, and internal-flow characteristics are provided.
Date: August 13, 1951
Creator: Dannenberg, Robert E.
Partner: UNT Libraries Government Documents Department
open access

Preliminary Investigation of the Transfer of Heat From a Flat Plate at a Mach Number of 1.5

Description: "Surface temperatures and heat transfer to the air stream have been measured for turbulent flow over a flat plate at a Mach number of 1.5 and at a Reynolds number, based on the momentum thickness of the boundary layer, of approximately 5000. Preliminary data are presented and the surface heat-transfer coefficients calculated from these data are considered to be accurate to plus or minus 2.6 percent at a temperature potential of 50 degrees Fahrenheit. These data are in good agreement with the re… more
Date: December 13, 1951
Creator: Emmons, M. A., Jr. & Blanchard, R. F.
Partner: UNT Libraries Government Documents Department
open access

Reduction of Carbon Dioxide inAqueous Solutions by IonizingRadiation

Description: The question of the conditions under which living matter originated on the surface of the earth is still a subject limited largely to speculation. The speculation has a greater chance of approaching the truth insofar as it includes and is based upon the ever wider variety of established scientific fact. One of the purposes of the herein reported observation was to add another fact to the ever increasing information which might have any bearing upon this most interesting question. It is not our … more
Date: March 13, 1951
Creator: Garrison, W. M.; Morrison, D. C.; Hamilton, J. G.; Benson, A. A. & Calvin, M.
Partner: UNT Libraries Government Documents Department
open access

A Relation of Wind Shear and Insolation to the Turbulence Encountered by an Airplane in Clear-Air Flight at Low Altitudes

Description: Memorandum presenting the observed gust experience of an airplane and information on the associated meteorological conditions to obtain a simple empirical relation for estimating the intensity of turbulence in the earth's friction layer. The relation does not discriminate between differences in turbulence intensity resulting from variations of flight altitude or diurnal variations of turbulence.
Date: September 13, 1951
Creator: Thompson, James K.
Partner: UNT Libraries Government Documents Department
open access

Removable Bowl Cold Trap

Description: No Description Available.
Date: August 13, 1951
Creator: Evans, E. C. & Babelay, E. F.
Partner: UNT Libraries Government Documents Department
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