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Fire Tests of Building Columns

Description: Technical paper issued by the Bureau of Mines over studies conducted on fire resistance on building columns. As stated in the introduction, "the purpose of this investigation is to ascertain (1) the ultimate resistance against fire, of protected and unprotected columns as used in the interior of buildings; (2) their resistance against impact and sudden cooling from hose streams when in a highly heated condition" (p. 12). This paper includes tables, illustrations.
Date: April 21, 1921
Creator: Ingberg, S. H.; Griffin, H. K.; Robinson, W. C. & Wilson, R. E.
Partner: UNT Libraries Government Documents Department
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Revision of the American Pikas (Genus Ochotona)

Description: Discusses distribution, habitat, habits, pelage, molt, specimens, history, and nomenclature of pikas. Provides descriptions, locations, and a key for species and subspecies.
Date: August 21, 1924
Creator: Howell, Arthur H.
Partner: UNT Libraries Government Documents Department
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Compressibilities of gases

Description: Reproduction of thirteen graphs for computing compressibilities of various gases and for computing the volumes delivered from cylinders containing various gases.
Date: November 21, 1925
Creator: Pickering, Samuel Fisher
Partner: UNT Libraries Government Documents Department
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Large-scale aerodynamic characteristics of airfoils as tested in the variable density wind tunnel

Description: From Summary: "In order to give the large-scale characteristics of a variety of airfoils in a form which will be of maximum value, both for airplane design and for the study of airfoil characteristics, a collection has been made of the results of airfoil tests made at full-scale values of the Reynolds number in the variable density wind tunnel of the National Advisory Committee for Aeronautics. They have been corrected for tunnel wall interference and are presented not only in the conventional form but also in a form which facilitates the comparison of airfoils and from which corrections may be easily made to any aspect ratio. An example showing the method of correcting the results to a desired aspect ratio has been given for the convenience of designers. In addition, the data have been analyzed with a view to finding the variation of the aerodynamic characteristics of airfoils with their thickness and camber."
Date: October 21, 1929
Creator: Jacobs, Eastman N. & Anderson, Raymond F.
Partner: UNT Libraries Government Documents Department
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Pressure Distribution Over a Thick, Tapered and Twisted Monoplane Wing Model-N.A.C.A. 81-J

Description: "This reports presents the results of pressure distribution tests on a thick, tapered and twisted monoplane wing model. The investigation was conducted for the purpose of obtaining data on the aerodynamic characteristics of the new wing and to provide additional information suitable for use in the design of tapered cantilever wings. The tests included angles of attack up to 90 degrees. The span loading over the wing was approximately of elliptical shape, which gave rise to relatively small bending moments about the root" (p. 97).
Date: May 21, 1930
Creator: Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department
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Combustion in a High-Speed Compression-Ignition Engine

Description: "An investigation conducted to determine the factors which control the combustion in a high-speed compression-ignition engine is presented. Indicator cards were taken with the Farnboro indicator and analyzed according to the tangent method devised by Schweitzer. The analysis show that in a quiescent combustion chamber increasing the time lag of auto-ignition increases the maximum rate of combustion. Increasing the maximum rate of combustion increases the tendency for detonation to occur" (p. 63).
Date: May 21, 1931
Creator: Rothrock, A. M.
Partner: UNT Libraries Government Documents Department
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The drag of airplane wheels, wheel fairings, and landing gears 2: nonretractable and partly retractable landing gears

Description: This is the second report giving the results obtained in the NACA 20-foot wind tunnel on the drag due to landing gears. The present report gives the results of tests of nonretractable and partly retractable landing gears intended for heavier low-wing monoplanes of the transport and bomber type.
Date: June 21, 1934
Creator: Biermann, David & Herrnstein, William H., Jr.
Partner: UNT Libraries Government Documents Department
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The drag of airplane wheels, wheel fairings, and landing gears - 3

Description: The tests reported in this report conclude the investigation of landing-gear drag that has been carried out in the NACA 20-foot wind tunnel. They supplement earlier tests (reported in Technical Report No. 485) made with full-scale dummy wheels, wheel fairings, and landing gears intended for airplanes of 3,000 pounds gross weight and include tests of tail wheels and tail skids.
Date: November 21, 1934
Creator: Herrnstein, William H., Jr. & Biermann, David
Partner: UNT Libraries Government Documents Department
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Spinning characteristics of wings 1: rectangular Clark Y monoplane wing

Description: "A series of wind tunnel tests of a rectangular Clark Y wing was made with the NACA spinning balance as part of a general program of research on airplane spinning. All six components of the aerodynamic force and moment were measured throughout the range of angles of attack, angles of sideslip, and values omega b/2v likely to be attained by a spinning airplane; the results were reduced to coefficient form. It is concluded that a conventional monoplane with a rectangular Clark y wing can be made to attain spinning equilibrium throughout a wide range of angles of attack but that provision of a yawing moment coefficient of -0.02 (against the spin) by the tail, fuselage, and interferences will insure against attainment of equilibrium in a steady spin" (p. 231).
Date: November 21, 1934
Creator: Bamber, M. J. & Zimmerman, C. H.
Partner: UNT Libraries Government Documents Department
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Wing-nacelle-propeller interference for wings of various spans force and pressure-distribution tests

Description: Report presents the results of an experimental investigation made in the NACA full-scale wind tunnel to determine the effect of wing span on nacelle-propeller characteristics and, reciprocally, the lateral extent of nacelle and propeller influence on a monoplane wing. The results provide a check on the validity of the previous research on nacelles and propellers with 15-foot-span wings tested in the 20-foot wind tunnel and reported in technical reports 415, 462, 505, 506, and 507.
Date: April 21, 1936
Creator: Robinson, Russell G. & Herrnstein, William H., Jr.
Partner: UNT Libraries Government Documents Department
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Span load distribution for tapered wings with partial-span flaps

Description: Tables are given for determining the load distribution of tapered wings with partial-span flaps placed either at the center or at the wing tips. Seventy-two wing-flap combinations, including two aspect ratios, four taper ratios, and nine flap lengths, are included. The distributions for the flapped wing are divided into two parts, one a zero lift distribution due primarily to the flaps and the other an additional lift distribution due to an angle of attack of the wing as a whole. Comparison between theoretical and experimental results for wings indicate that the theory may be used to predict the load distribution with sufficient accuracy for structural purposes.
Date: November 21, 1936
Creator: Pearson, H. A.
Partner: UNT Libraries Government Documents Department
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Tests in the variable-density wind tunnel of the NACA 23012 airfoil with plain and split flaps

Description: From Summary: "Section characteristics for use in wing design are presented for the NACA 23012 airfoil with plain and split flaps of 20 percent wing chord at a value of the effective Reynolds number of about 8,000,000. The flap deflections covered a range from 60 degrees upward to 75 degrees downward for the plain flap and from neutral to 90 degrees downward for the split flap. The split flap was aerodynamically superior to the plain flap in producing high maximum lift coefficients and in having lower profile-drag coefficients at high lift coefficients."
Date: January 21, 1938
Creator: Abbott, Ira H. & Greenberg, Harry
Partner: UNT Libraries Government Documents Department
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Purification of Uranium Oxide

Description: No Description Available.
Date: April 21, 1942
Creator: Hoffman, J.I.
Partner: UNT Libraries Government Documents Department
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Analysis of Heat and Compressibility Effects in Internal Flow Systems and High-Speed Tests of a Ram-Jet System

Description: Report discussing an analysis has been made by the NACA of the effects of heat and compressibility in the flow through the internal systems of aircraft along with equations and charts are developed whereby the flow characteristics at key stations in a typical internal system may be readily obtained.
Date: July 21, 1942
Creator: Becker, John V. & Baals, Donald D.
Partner: UNT Libraries Government Documents Department
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Chemical Research -- U233 Production and Extraction; Report for the Month Ending June 21, 1943

Description: Abstract. The precipitation of Pa233 with MnO2 from a solution of thorium nitrate has been studied in some detail and seems quite satisfactory up to 36 gm Th(HO3)4 4H2O per 100 cc solution. The concentration of Pa233 with respect to the manganese dioxide carrier and the thorium precipitated with the carrier appears to be accomplished quite well by either a series of MnO2 cycles or thorium iodate cycles. Volatility methods for both the separation of Pa233 from the original thorium and for its separation from MnO2 are now under investigation. It has been decided that thorium carbonate will the the thorium compound used in the pile at Site X.
Date: June 21, 1943
Creator: Franck, J.
Partner: UNT Libraries Government Documents Department
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Measurements of the flying qualities of a Bell P-39D-1 airplane (AAF NO. 41-28378)

Description: Report discussing an investigation of the flight qualities of the Bell P-39D-1 airplane. Information about the longitudinal stability and control characteristics, lateral and directional stability and control, stalling characteristics, and control friction is provided.
Date: September 21, 1943
Creator: Johnson, Harold I.; Liddell, C. J. & Hoover, H. H.
Partner: UNT Libraries Government Documents Department
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Determination of Free Nitric Acid in UNH Solutions, Problem Assignment No. 208-X2A, Progress Report

Description: Technical report abstract: Since UNH is a highly dissociated compound which ionizes to NO3 and (UO2), the latter ion being very weakly basic, a solution of pure UNH is quite acid (pH about 3). It is possible to titrate to a phenolphthalein and point with standard caustic solution and obtain a figure which represents the free acid plus the NO3 from the the UNH. However, titration of the free nitric acid alone in such a solution presents quite a problem. By precipitating and removing uranium from solution by means of potassium ferrocyanide, the residual free acid may be titrated directly by means of standard caustic using either methyl red or phenolphthalein indicators, with an error of less than 4%. A method is given to determine formic acid, should that acid be present in the mixture.
Date: April 21, 1944
Creator: Parlour, A. K. & Hammond, C. W.
Partner: UNT Libraries Government Documents Department
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Hanford Engineer Works, technical progress letter number 15, October 13 through October 19, 1944

Description: This report documents the progress made for the week in each of the following areas: fuel canning operations; reactor operations (100 area); instrumentation development; and fuel reprocessing (200 area). Detailed information is given for each of these areas. Problems encountered are also discussed.
Date: October 21, 1944
Creator: Bugbee, S. J.
Partner: UNT Libraries Government Documents Department
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Knock-Limited Performance of Blends of AN-F-28 Fuel Containing 2 Percent Aromatic Amines 4

Description: Report discussing tests on the effect of 2-percent additions of 13 aromatic amines on the knock-limited performance of 28-R fuel in a CFR engine. The amines tested gave good rich mixture response at standard F-4 operating conditions, but were sensitive to engine severity at lean fuel-air ratios.
Date: December 21, 1944
Creator: Alquist, Henry E. & Tower, Leonard K.
Partner: UNT Libraries Government Documents Department
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Relation Between Fuel Economy and Crank Angle for the Maximum Rate of Pressure Rise

Description: Report discussing an investigation to determine whether the crank angle for maximum rate of pressure rise can be used to indicate maximum-economy spark advance. Information about spark-advance tests at constant inlet-air pressure and fuel-air-ratio test results are provided.
Date: May 21, 1945
Creator: Cook, Harvey A. & Brightwell, Virginia L.
Partner: UNT Libraries Government Documents Department
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300 Area: December 11 Through December 17

Description: This report discusses the operation of the Hanford Reservation`s 300 Area for December 11 through December 17, 1945. They discuss: extrusion, canning, slug testing, a magnesium chloride flux, and the composition changes of a aluminium-silicon dip bath.
Date: December 21, 1945
Partner: UNT Libraries Government Documents Department
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