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The Armstrong Whitworth A.W. 16 Military Airplane (British): A Single-Seat Biplane

Description: Circular presenting a description of the A.W. XVI, which is a single-bay staggered biplane of metal construction with a clean external design. A description of the tail unit, control system, cockpit, fuselage, characteristics, performance, drawings, and photographs are provided.
Date: January 1932
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Unsteady Lift of a Finite Wing

Description: Note discussing the lift of a finite wing including the calculations and constants for each step of the lift. This information is compared against the lift of an infinite wing. From Summary: "Unsteady lift function for wings of finite aspect ratio have been calculated by approximate methods involving corrections of the aerodynamic inertia and of the angle of the infinite wing. The starting lift of the finite wing is found to be only slightly less than that of the infinite wing; whereas the fina… more
Date: January 1939
Creator: Jones, Robert T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Pressure drop in tank and float vent tubes on diving airplanes

Description: Report presenting an experiment regarding tank and float venting conditions that exist on diving airplanes undergoing rapid changes in altitude. The results indicated that large pressure differences build up between the outside and inside of tanks and floats on diving airplanes unless the correct size of venting tube is used.
Date: January 1939
Creator: Waldron, C. D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Clerget 100 Hp Heavy-Oil Engine

Description: A complete technical description of the Clerget heavy-oil engine is presented along with the general characteristics. The general characteristics are: 9 cylinders, bore 120 mm, stroke 130 mm, four-stroke cycle engine, rated power limited to 100 hp at 1800 rpm; weight 228 kg; propeller with direct drive and air cooling. Moving parts, engine block, and lubrication are all presented.
Date: January 1931
Creator: Léglise, Pierre
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Combating Airplane Fires

Description: This report provides a summary of the important steps to be taken in combating airplane fires. Some considerations and ways of preventing fires from developing are provided.
Date: January 1930
Creator: Brunat, Henri
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Engineering Report on Oklahoma City Oil Field, Oklahoma

Description: Report issued by the U.S. Bureau of Mines on the engineering and production methods of the Oklahoma City oil wells. Characteristics and properties of the wells, and methods and practices of well engineering are presented. This report includes tables, graphs, maps, and illustrations.
Date: January 1937
Creator: Hill, Harry Blackburn; Rawlins, E. L. & Bopp, C. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Study of Oxidation of the Oil in Two Air-and Air-Gas-Repressuring Projects

Description: Report issued by the U.S. Bureau of Mines on the oxidation levels caused from different oil recovery processes. Experiments were conducted to determine the effect of air on crude oil, and the degree of oxidation. This report includes tables, and a map.
Date: January 1937
Creator: Johnson, T. W. & Taylor, Sam S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Coal-Mine Fatalities in December, 1930

Description: Report issued by the U.S. Bureau of Mines on the coal mine related deaths during December, 1930. The number of fatalities and the causes are presented. This report includes tables.
Date: January 1931
Creator: Adams, William Waugh & Chenoweth, L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Coefficients of Flow of Standard Nozzles

Description: We first undertook experiments with air, devoted principally to the investigation of the disturbances due to the differences in the nature of the flow to the nozzle. The difficulty of measuring the air, however, caused us to experiment with water. Due to the possibility of measuring the capacity of the container, this method was much more accurate than measuring with Pitot tobes.
Date: January 1930
Creator: Mueller, H. & Peters, H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Resistance of Plates and Pipes at High Reynolds Numbers

Description: It was learned that the law of resistance for high R values does not follow the simple powers, and that the powers, which can be obtained approximately for the velocity distribution, gradually change. Since, moreover, very important investigations have recently been made on the resistance of plates at very high R values, it seemed of interest to apply the above line of reasoning to the new general law of resistance. For this purpose, the resistance and velocity distribution along the plate must… more
Date: January 1931
Creator: Schiller, L. & Hermann, R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Contribution to the Study of Normal Burning in Gaseous Carbureted Mixtures: Part 1

Description: In the present study it is proposed to provide an equipment permitting the study of the propagation of the region of reaction in mixtures of air and carbureted gases enclosed within a cylinder. Ignition is produced at the end of compression by an electric spark. With this apparatus it is proposed to determine: 1) the influence of the richness of the explosive mixture on the rate of flame propagation; 2) the influence of the degree of volumetric compression on one of the hydrocarbons; 3) the inf… more
Date: January 1930
Creator: Duchene, M. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Turbulence and Mechanism of Resistance on Spheres and Cylinders

Description: The nature of turbulent flow through pipes and around obstacles is analyzed and illustrated by photographs of turbulence on screens and straighteners. It is shown that the reversal of flow and of the resistance law on spheres is not explainable by Prandtl's turbulence in the boundary layer. The investigation of the analogous phenomena on the cylinder yields a reversal of the total field of flow.
Date: January 1932
Creator: Ahlborn, F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Dynamic Testing of Airplane Shock-Absorbing Struts

Description: "Measurement of perpendicular impacts of a landing gear with different shock-absorbing struts against the drum testing stand. Tests were made with pneumatic shock absorbers having various degrees of damping, liquid shock absorbers, steel-spring shock absorbers and rigid struts. Falling tests and rolling tests. Maximum impact and gradual reduction of the impacts in number and time in the falling tests. Maximum impact and number of weaker impacts in rolling tests" (p. 1).
Date: January 1932
Creator: Langer, P. & Thomé, W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Structural Details of the Giant Dornier Seaplane "Do X."

Description: Memorandum presenting a description of the Dornier seaplane Do X. Details of the general description, materials, details of the main wing and upper wing, details of the hull and of the wing stubs, tail surfaces and control lines, power plant, and launching car and floating dock are provided.
Date: January 1930
Creator: Gustosa, Corrado
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The effect of trim angle on the take-off performance of a flying boat

Description: From Summary: "Data obtained at the N.A.C.A. tank from tests on the models of three flying-boat hulls - N.A.C.A. models 11-A, 16, and 22 - are used to demonstrate the effect of trim angle on water resistance. A specific example is taken, and data from Model 11-A are used to show that the trim angle giving the minimum water resistance will give minimum total air-plus-water resistance. Total-resistance curves for best trimmed angles and other angles are compared for the same example."
Date: January 1934
Creator: Shoemaker, James M. & Dawson, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tests of three tapered airfoils based on the N.A.C.A. 2200, the N.A.C.A.-M6, and the Clark Y sections

Description: Three tapered airfoils based on the N.A.C.A. 2200, the N.A.C.A.-M6, and the Clark Y sections were tested in the variable-density wind tunnel at a Reynolds Number of approximately 3,100,000. The models, which were of aspect ratio 6, had constant core center sections and rounded tips, and tapered in thickness from 18 percent at the roots to 9 percent at the tips. The aerodynamic characteristics are given by the usual dimensionless coefficients plotted for both positive and negative angles of atta… more
Date: January 1934
Creator: Anderson, Raymond F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Strain Measurements on Small Duralumin Box Beams in Bending

Description: "Extensive strain-gage measurements were made chiefly on the tension side of five small rectangular box beams constructed of sheet duralumin. The main conclusion was that within the test range the tension cover may be considered as being fully effective but that at any given point on the beam there may be unaccountable variations of 5 percent from the calculated stresses on the thicker sheets tested (0.044 and 0.023 inch) and of 10 percent or more on the thinnest sheet tested (0.014 inch)" (p. … more
Date: January 1937
Creator: Kuhn, Paul
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Tests of Carburetor-Intake Rams

Description: "An investigation was conducted in the NACA 20-foot wind tunnel of the ramming effect of three general types of carburetor intake rams for radial engines, namely, the internal constant area type, the external constant area type, and the external expanding type. The rams were installed on a radial air- cooled engine nacelle, and tests were made with and without the propeller operating. The results indicated that the external types having entrances near the front of the engine cowling gave the gr… more
Date: January 1938
Creator: Highley, Frank H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Improvement of aileron effectiveness by the prevention of air leakage through the hinge gap as determined in flight

Description: "A flight investigation was made of the increase in effectiveness of ailerons that can be obtained by preventing flow of air through the wing at the hinges and of the possibility of reducing the aileron operating force by replacing ailerons having normal open hinge gaps with narrower but equally effective ailerons having sealed hinge gaps. Tests were made with a Fairchild 22 airplane with two sizes of plain unbalanced ailerons, one set having a chord equal to 0.18c, and the other chord equal to… more
Date: January 1938
Creator: Soulé, H. A. & Gracey, W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Spinning characteristics of wings 5: N.A.C.A. 0009, 23018, and 6718 monoplane wings

Description: Three rectangular monoplane wings having rounded tips were tested on the N.A.C.A. spinning balance in the 5-foot vertical wind tunnel. The airfoil sections used were the N.A.C.A. 0009, 23018, and 6718. The aerodynamic characteristics of the models and a prediction of the angles of sideslip for steady spins are given. There is included an estimate of the yawing moment that must be furnished by parts of the airplane to balance the inertia couples and wing yawing moments for spinning equilibrium. … more
Date: January 1938
Creator: Bamber, M. J. & House, R. O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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