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Iron Oxide Reduction Equilibria: A Critique from the Standpoint of the Phase Rule and Thermodynamics

Description: Report issued by the Bureau of Mines over studies conducted on iron oxide reduction. As stated in the scope of bulletin, "this bulletin, therefore, presents the properties of the common oxides of iron, their combinations with each other, and the reduction-equilibrium diagrams by which the investigator passes from one to the next; the end point is not pure iron but the carburized iron of the blast furnace, cast iron" (p. 1-2). This report includes tables, and illustrations.
Date: 1929
Creator: Ralston, Oliver C.
Partner: UNT Libraries Government Documents Department
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Petroleum Refinery Statistics: 1927

Description: Report issued by the Bureau of Mines over statistical records kept on petroleum refineries during 1927. Statistical information on different forms of petroleum is discussed. This report includes tables.
Date: 1929
Creator: Hopkins, G. R.
Partner: UNT Libraries Government Documents Department
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Facts Relating to the Production and Substitution of Manufactured Gas for Natural Gas

Description: Report issued by the Bureau of Mines over information obtained on manufactured gas production instead of natural gas production. The information collected is discussed. This includes such topics as rates, methods, and locations of gas. This report includes tables, maps, illustrations, and photographs.
Date: 1929
Creator: Odell, William Wallace
Partner: UNT Libraries Government Documents Department
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Flow of Gases Through Beds of Broken Solids

Description: Report issued by the Bureau of Mines over studies conducted on the effects of vapor flow through beds of broken solids. Methods and results of the studies are presented and discussed. This report includes tables, illustrations, and photographs.
Date: 1929
Creator: Furnas, C. C.
Partner: UNT Libraries Government Documents Department
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The Drag and Interference of a Nacelle in the Presence of a Wing

Description: A wing interference investigation was conducted to determine why the N.A.C.A. cowling did not yield the expected increase in speed when adapted to the outboard nacelles of trimotored airplanes. The results indicate that the drag and interference of the engine nacelle with the cowling, when combined with a thick wing, can be reduced from its value as originally applied by changing its position and fairing it into the wing.
Date: October 1929
Creator: Jacobs, Eastman N.
Partner: UNT Libraries Government Documents Department
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The Impact on Seaplane Floats During Landing

Description: "In order to make a stress analysis of seaplane floats, and especially of the members connecting the floats with the fuselage, it is of great importance to determine the maximum pressure acting on the floats during landing. Here, the author gives a formula for maximum pressures during landing that permits one to apply experimental results to different bodies and different velocities. The author notes that the formula checks very well with experimental results" (p. 1).
Date: October 1929
Creator: von Karman, T.
Partner: UNT Libraries Government Documents Department
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The effect of the wings of single engine airplanes on propulsive efficiency as shown by full scale wind tunnel tests

Description: An investigation was conducted to determine the effect of the wings on propulsive efficiency. The wings are shown to cause a reduction of 1 percent to 3 percent in propulsive efficiency, which is about the same for monoplane as well as biplane wings.
Date: October 1929
Creator: Weick, Fred E. & Wood, Donald H.
Partner: UNT Libraries Government Documents Department
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Spiral Tendency in Blind Flying

Description: "The flight path followed by an airplane which was being flown by a blindfolded pilot was observed and recorded. When the pilot attempted to make a straight-away flight there was a tendency to deviate from the straight path and to take up a spiral one" (p. 1).
Date: August 1929
Creator: Carroll, Thomas & McAvoy, William H.
Partner: UNT Libraries Government Documents Department
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Viscosity of diesel engine fuel oil under pressure

Description: In the development of Diesel engine fuel injection systems it is necessary to have an approximate knowledge of the absolute viscosity of the fuel oil under high hydrostatic pressures. This report presents the results of experimental tests conducted by Mr. Jackson Newton Shore, utilizing the A.S.M.E. high pressure equipment.
Date: September 1929
Creator: Hersey, Mayo D.
Partner: UNT Libraries Government Documents Department
open access

Wind Tunnel Tests on a Model of a Monoplane Wing with Floating Ailerons

Description: This report describes preliminary wind tunnel tests on a model of a monoplane wing equipped with wing tip floating ailerons. Lift and drag, as well as rolling and yawing moments, were measured.
Date: September 1929
Creator: Knight, Montgomery & Bamber, Millard J.
Partner: UNT Libraries Government Documents Department
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Tests of Four Racing Type Airfoils in the Twenty-Foot Propeller Research Tunnel

Description: Tests were made on four racing type airfoils, the N-9, N-38, C-62, and N-46, in order to determine the high speed characteristics of the wings. The results indicate that the N-46 has about 12 percent lower minimum drag than the regular C-62 section, and that both the N-38 and N-46 have the same exceptionally low minimum drag coefficient.
Date: September 1929
Creator: Weick, Fred E.
Partner: UNT Libraries Government Documents Department
open access

Full Scale Investigation of the Drag of a Wing Radiator

Description: Tests were made on the 1927 Williams racer in order to determine the effect of the wing radiator on the airfoil characteristics. It was found that the radiator doubled the minimum drag of the portion of the wing it covered, and also reduced the lift somewhat.
Date: September 1929
Creator: Weick, Fred E.
Partner: UNT Libraries Government Documents Department
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Curves Showing Column Strength of Steel and Duralumin Tubing

Description: Given here are a set of column strength curves that are intended to simplify the method of determining the size of struts in an airplane structure when the load in the member is known. The curves will also simplify the checking of the strength of a strut if the size and length are known. With these curves, no computations are necessary, as in the case of the old-fashioned method of strut design. The process is so simple that draftsmen or others who are not entirely familiar with mechanics can c… more
Date: May 1929
Creator: Ross, Orrin E.
Partner: UNT Libraries Government Documents Department
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Wind tunnel pressure distribution tests on a series of biplane wing models Part II: effects of changes in decalage, dihedral, sweepback and overhang

Description: This preliminary report furnishes information on the changes in the forces on each wing of a biplane cellule when the decalage, dihedral, sweepback and overhang are separately varied. The data were obtained from pressure distribution tests made in the Atmospheric Wind Tunnel of the Langley Memorial Aeronautical Laboratory. Since each test was carried up to 90 degree angle of attack, the results may be used in the study of stalled flight and of spinning and in the structural design of biplane wi… more
Date: October 1929
Creator: Knight, Montgomery & Noyes, Richard W.
Partner: UNT Libraries Government Documents Department
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Strength of Tubing Under Combined Axial and Transverse Loading

Description: Note presenting a systematic study of the strength of duralumin and chrome-molybdenum steel round tubing in combined transverse and axial loading. A description of the formulas that are the groundwork for the study as well as the results of the tests are provided.
Date: June 1929
Creator: Tuckerman, L. B.; Petrenko, S. N. & Johnson, C. D.
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Pressure Distribution Tests on an Airfoil With Trailing Edge Flap

Description: "This report deals with pressure distribution tests on an airfoil with a conventional trailing edge flap. These tests were conducted in the Atmospheric Wind Tunnel of the National Advisory Committee for Aeronautics. Maximum chord loadings were obtained with the flap displaced downward and with the airfoil at large angles of attack. Greater changes were produced in the normal force and in the center of pressure travel by up-flap than by an equal down-flap displacement" (p. 1).
Date: October 1929
Creator: Wenzinger, Carl J. & Loeser, Oscar, Jr.
Partner: UNT Libraries Government Documents Department
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Pressure Distribution on a Slotted R.A.F. 31 Airfoil in the Variable Density Wind Tunnel

Description: Measurements were made in the variable density wind tunnel to determine the pressure distribution over one section of a R.A.F. 31 airfoil with a leading edge slot fully open. To provide data for the study of scale effect on this type of airfoil, the tests were conducted with air densities of approximately one and twenty atmospheres.
Date: June 1929
Creator: Jacobs, Eastman N.
Partner: UNT Libraries Government Documents Department
open access

Some Studies on the Aerodynamic Effect of the Gap Between Airplane Wings and Fuselages

Description: "The general result indicated by this study is that if desirable from any viewpoint the gap between wing and fuselage may be closed without detrimental aerodynamic effects, and with a given monoplane there is less drag if the wing is directly on top of the fuselage than if it is parasol" (p. 1).
Date: November 1929
Creator: Ober, Shatswell
Partner: UNT Libraries Government Documents Department
open access

Correcting Engine Tests for Humidity

Description: Note presenting tests using a multicylinder engine to determine the effect that atmospheric humidity has on some phases of engine performance. Three test series with different types of fuel were carried out. The results indicate that failure to allow for the effect of differences in atmospheric humidity may introduce errors as great as would be occasioned by failure to allow for changes in barometric pressure.
Date: June 1929
Creator: Brooks, Donald B.
Partner: UNT Libraries Government Documents Department
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The Effect of Fuel Consumption on Cylinder Temperatures and Performance of a Cowled Wright J-5 Engine

Description: Given here are the results of tests made to determine the effect of fuel consumption on the cylinder temperatures and the performance of a cowled Wright J-5 engine. The results of these tests indicate that enriching the mixture by increasing the carburetor size results in a reduction in cylinder head and barrel temperatures. The cylinders shielded by the magnetos or the points on the cylinder that do not receive a free flow of cooling air increase most rapidly in temperature as the mixture is l… more
Date: November 1929
Creator: Schey, Oscar W.
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Tests on Airfoil Boundary Control Using a Backward Opening Slot (1929)

Description: "This report presents the results of an investigation to determine the effect of boundary layer control on the lift and drag of an airfoil equipped with a backward opening slot. Various slot locations, widths of opening, and pressures, were used. The tests were conducted in the Five-Foot Atmospheric Wind Tunnel of the Langley Memorial Aeronautical Laboratory" (p. 1).
Date: October 1929
Creator: Knight, Montgomery & Bamber, Millard J.
Partner: UNT Libraries Government Documents Department
open access

Wind Tunnel Tests on an Airfoil Equipped With a Split Flap and a Slot

Description: "The investigation described in this report is concerned with the changes in the aerodynamic characteristics of an airfoil which are produced by a gauze-covered suction slot, located near the leading edge, and connected by an air passage to a split flap at the trailing edge. The tests were conducted at the Langley Memorial Aeronautical Laboratory. At the larger values of lift coefficient where the action of the slot might be expected to be most effective, the pressure differences were such that… more
Date: October 1929
Creator: Bamber, Millard J.
Partner: UNT Libraries Government Documents Department
open access

A New Method for the Prediction of Airplane Performance

Description: A new method for the prediction of airplane performance in level and climbing flight, together with complete information regarding propeller speeds, is described in this report. Developed from Bairstow's system and making use of American absolute coefficients, this method has advantages of simplicity and brevity.
Date: February 1929
Creator: Lesley, E. P. & Reid, E. G.
Partner: UNT Libraries Government Documents Department
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