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The British Klemm "Eagle" Commercial Airplane: A Low-Wing Cantilever Monoplane

Description: Circular presenting a description of the British Klemm "Eagle", which is a low-wing commercial cantilever monoplane. Details of the components, flying qualities, design characteristics, weights and loadings, drawings, and photographs are provided.
Date: August 1934
Partner: UNT Libraries Government Documents Department
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D.H. 86 "Express Air Liner" (British): A Four-Engine Biplane

Description: Circular describing the De Havilland Express Air Liner, which is a four-engine two-bay biplane of clean and well-streamlined form. Details of the cabin, controls, fuselage, tail, wings, engines, cockpit, characteristics, performance, drawings, and photographs are provided.
Date: April 1934
Partner: UNT Libraries Government Documents Department
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The Avia 51 Commercial Airplane (Czechoslovakian): A Cantilever High-Wing Monoplane

Description: Circular describing the Avia 51 commercial airplane, which is a Czechoslovakian cantilever high-wing monoplane with a fairly orthodox design. Details of the performance, construction, wing, ailerons, fuselage, landing gear, engines, characteristics, drawings, and photographs are provided.
Date: February 1934
Partner: UNT Libraries Government Documents Department
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The Short "Scylla" Commercial Airplane (British): An All-Metal Biplane

Description: Circular presenting a description of the Short Scylla, which is a 39-passenger landplane with four Bristol Jupiter XF BM engines. A description of the characteristics, blueprints, and photographs of the aircraft are provided.
Date: May 1934
Partner: UNT Libraries Government Documents Department
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Fokker F.XX Commercial Airplane (Dutch): A High-Wing Cantilever Monoplane

Description: Circular describing the Fokker F.XX, which is a three-engine high-wing cantilever monoplane with retractable landing gear and tail wheel. Details of the wing, fuselage, cockpit, cabin, covering and cowling, control surfaces, landing gear, power plant, fuel and oil systems, characteristics, drawings, and photographs are provided.
Date: February 1934
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Investigation of a Cup Anemometer

Description: Results of an investigation wherein the change of the normal force coefficient with Reynolds Number was obtained statically for a 15.5-centimeter hemispherical cup.
Date: July 1934
Creator: Hubbard, John D. & Brescoll, George P.
Partner: UNT Libraries Government Documents Department
open access

Avro 642 Commercial Airplane (British): A High-Wing Cantilever Monoplane

Description: Circular describing the Avro 642, which is a mixed construction high-wing cantilever monoplane. Details of the engines, controls, interior, wings, cockpit, ailerons, landing gear, characteristics, performance, drawings, and photographs are provided.
Date: May 1934
Partner: UNT Libraries Government Documents Department
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The Avro "Commodore" Touring Airplane (British): A Cabin Biplane

Description: Circular describing the Avro Commodore, which is a cabin biplane of metal construction that is designed for comfort rather than performance. Details regarding the fuselage, wings, landing gear, controls, characteristics, drawings, and photographs are provided.
Date: July 1934
Partner: UNT Libraries Government Documents Department
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The De Havilland "Comet" Long-Range Airplane (British): A Low-Wing Cantilever Monoplane

Description: Circular describing the De Havilland Comet, which is a long-range airplane that has been designed for the England-Australia race and was constructed using a stressed-skin construction. Details of the fuselage, landing gear, design, drawings, and photographs are provided.
Date: October 1934
Partner: UNT Libraries Government Documents Department
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The Bernard 82 Military Airplane (French): A Long-Range Monoplane

Description: Circular presenting a description of the Bernard 82, which is a scaled-up version of the 80 G.R.; they have similar designs but the 82 has greater span and wing area, deeper chord, higher fuselage, and a thicker wing for the bombs. A description of some flight tests and characteristics is also provided.
Date: June 1934
Partner: UNT Libraries Government Documents Department
open access

The Occurrence of Gases in Coals

Description: Report issued by the U.S. Bureau of Mines on the different types of gases that are present in coal. Theories behind why these gases occur in coal are presented. This report includes tables and graphs.
Date: June 1934
Creator: Selden, R. F.
Partner: UNT Libraries Government Documents Department
open access

Tabulated Analyses of Texas Crude Oils

Description: Report issued by the U.S. Bureau of Mines covering the crude oils from different regions of Texas. Analysis of the properties of each oil sample from the different regions of the state are presented. This report includes tables, and a map.
Date: December 1934
Creator: Wade, Gustav
Partner: UNT Libraries Government Documents Department
open access

Analyses of Crude Oils From Some Fields of Southern Louisiana

Description: Report issued by the U.S. Bureau of Mines on the studies of crude oil samples collected from southern Louisiana. The properties of each sample are analyzed. This report includes tables.
Date: November 1934
Creator: Kraemer, A. J. & Garton, E. L.
Partner: UNT Libraries Government Documents Department
open access

United States Earthquakes, 1934

Description: Report discussing earthquake activity in the United States during 1934. The report is broken down by regions and has sections for specific earthquakes.
Date: 1934
Partner: UNT Libraries Government Documents Department
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The high-speed tank of the Hamburg Shipbuilding Company

Description: A description of the Hamburg tank and carriage is provided as well as a layout of the control station and generator room.
Date: February 1934
Creator: Kempf, G. & Sottorf, W.
Partner: UNT Libraries Government Documents Department
open access

General Theory of Aerodynamic Instability and the Mechanism of Flutter

Description: "The aerodynamic forces on an oscillating airfoil or airfoil-aileron combination of three independent degrees of freedom were determined. The problem resolves itself into the solution of certain definite integrals, which were identified as Bessel functions of the first and second kind, and of zero and first order. The theory, based on potential flow and the Kutta condition, is fundamentally equivalent to the conventional wing section theory relating to the steady case" (p. 291).
Date: May 2, 1934
Creator: Theodorsen, Theodore
Partner: UNT Libraries Government Documents Department
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A complete tank test of a flying-boat hull with a pointed step - N.A.C.A. Model No. 22

Description: "The results of a complete tank test of a model of a flying-boat hull of unconventional form, having a deep pointed step, are presented in this note. The advantage of the pointed-step type over the usual forms of flying-boat hulls with respect to resistance at high speeds is pointed out. A take-off example using the data from these tests is worked out, and the results are compared with those of an example in which the test data for a hull of the type in general use in the United States are appl… more
Date: February 1934
Creator: Shoemaker, James M.
Partner: UNT Libraries Government Documents Department
open access

Effect of Retractable-Spoiler Location on Rolling- and Yawing-Moment Coefficients

Description: "In this report are presented the results of wind-tunnel tests of retractable spoilers on the upper surface of a Clark Y wing, which have been made as part of an investigation of lateral control devices being conducted by the National Advisory Committee for Aeronautics. Spoilers with chords up to 15.0 percent of the wing chord were tested in several locations on a plain rectangular wing and in two locations on the same wing equipped with a 20.0 percent chord split flap down 60 degrees. Charts a… more
Date: July 1934
Creator: Shortal, J. A.
Partner: UNT Libraries Government Documents Department
open access

Full-scale drag tests of landing lamps

Description: "Drag tests were conducted in the N.A.C.A. full-scale wind tunnel on full-scale models of two Army Air Corps type A-6 landing lamps mounted on an 8 by 48 foot airfoil. Drag measurements were made with the lamps in the leading edge and attached to the lower surface at the 5 and 10 percent chord positions. The drag of the lamps when faired into the airfoil was also measured. The results show that at 100 miles per hour and at the angle of minimum drag of the airfoil the unaired lamps in the leadin… more
Date: May 1934
Creator: Dearborn, C. H.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Measurements of Air Loads on Split Flaps

Description: Note presenting tests in a wind tunnel to determine the control forces and air loads acting on split flaps. Clark Y wing models were used with two different sizes of full-span split flaps, one with a medium chord and one with a narrow chord. The results indicated that at angles of attack and flap deflections for maximum lift, the lift loads on the split flaps were only 5 percent and 9 percent of the total lift for the narrow and medium-chord flaps respectively.
Date: May 1934
Creator: Wenzinger, Carl J.
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.
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.
Partner: UNT Libraries Government Documents Department
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