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"Avimeta" Three-Engine Commercial Monoplane: Type A.V.M. 132
This is an all metal aircraft, including the wing coverings. Both the framework and the sheet-metal coverings are Alferium, made by Schneider Co. A description of the wing, fuselage, landing gear, engines, fuel tanks, characteristics, drawings, and photographs are provided.
Date:
December 1927
Creator:
unknown
System:
The UNT Digital Library
The Fiat "TR.1" Training and Touring Airplane (Italian): A Two-Place High-Wing Monoplane
Circular presenting a description of the Fiat T.R.1 airplane, which has been created for training and long-distance touring. Information regarding the fuel tanks, aircraft design, controls, tail characteristics, and flight characteristics is provided.
Date:
December 1930
Creator:
unknown
System:
The UNT Digital Library
The Morane Sauliner 222 Airplane (French): A Single-Seat Pursuit Monoplane
Circular presenting the Morane Saulnier 222 airplane, which is a single-seat pursuit monoplane. A description of the components, design, characteristics, performance, photographs, and drawings are provided.
Date:
December 1929
Creator:
Frachet, André
System:
The UNT Digital Library
Albert TE-1 Training Airplane
The TE-1 is designed for the economical training of pilots and is a single seat parasol cantilever monoplane. It is nearly entirely made of wood, using a 40 HP. air-cooled Salmson A.D. 9 engine, and weighs 255 kg empty.
Date:
December 1926
Creator:
unknown
System:
The UNT Digital Library
A method for determining the rate of heat transfer from a wing or streamline body
From Summary: "A method for calculating the rate of heat transfer from the surface of an airfoil or streamline body is presented. A comparison with the results of an experimental investigation indicates that the accuracy of the method is good. This method may be used to calculate the heat supply necessary for heat de-icing or in ascertaining the heat loss from the fuselage of an aircraft operating at great altitude, for example."
Date:
December 1942
Creator:
Frick, Charles W., Jr. & McCullough, George B.
System:
The UNT Digital Library
Tests of a Thermal Ice-Prevention System for a Wing Leading-Edge Landing-Light Installation
Report discussing the creation of a thermal ice-prevention system of a bomber-type airplane to provide protection against ice and fog formations on the transparent fairing over the landing light in the wing leading edge. A comparison between the design performance and actual performance showed that the outer-surface heat-transfer coefficient was correctly predicted, but the inner-surface heat-transfer coefficient was four times as large, leading to failure of the plastic fairing.
Date:
December 1944
Creator:
Hillendahl, Wesley H.
System:
The UNT Digital Library
The D.H. 85 "Leopard Moth" Airplane (British): A Three-Seat Cabin High-Wing Monoplane
Circular describing the De Havilland "Leopard Moth", which is a three-seat cabin high-wing monoplane with a good cruising speed and fuel efficiency. Details of the components, controls, characteristics, performance, drawings, and photographs are provided.
Date:
December 1933
Creator:
unknown
System:
The UNT Digital Library
Performance of an exhaust-gas "blowdown" turbine on a nine-cylinder radial engine
Report presenting tests on an exhaust-gas turbine with four separate nozzle boxes each covering a 90 degree arc of the nozzle diaphragm and each connected to a pair of adjacent cylinders in a Pratt & Whitney R-1340-12 nine-cylinder radial engine. Results regarding the power output of the engine and turbine, effect of the turbine on engine power, turbine power output and speed characteristics, mean turbine efficiency, effect of the blowdown turbine on exhaust-gas temperature, and condition of the blowdown turbine after tests are provided.
Date:
December 1944
Creator:
Turner, L. Richard & Desmon, Leland G.
System:
The UNT Digital Library
The Short "Empire" Commercial Flying Boat (British): An All-Metal Cantilever Monoplane
Circular presenting a description of the Short "Empire" flying boat, which is an all-metal, four-engine, cantilever monoplane with a two-step hull.
Date:
December 1936
Creator:
unknown
System:
The UNT Digital Library
The Dewoitine D.332 Commercial Airplane (French): A Three-Engine All-Metal Low-Wing Monoplane
Circular describing the Dewoitine D.332, which is a commercial three-engine all-metal low-wing monoplane form France. Details of the construction history, wing, fuselage, power plant, landing gear, characteristics, performance, drawings, and photographs are provided.
Date:
December 1933
Creator:
Victor, Maurice
System:
The UNT Digital Library
A method for calculating heat transfer in the laminar flow region of bodies
Report presenting a practical method for determining the chordwise distribution of the rate of heat transfer from the surface of a wing or body of revolution to air. The method is limited to use to the determination of heat transfer fro the forward section of such bodies when the flow is laminar.
Date:
December 1942
Creator:
Allen, H. Julian & Look, Bonne C.
System:
The UNT Digital Library
Calculations of Economy of 18-Cylinder Radial Aircraft Engine With Exhaust-Gas Turbine Geared to the Crankshaft at Cruising Speed
Report presenting calculations based on dynamometer test-stand data on an 18-cylinder radial engine made to determine the improvement in fuel consumption that can be obtained by gearing an exhaust-gas turbine to the engine crankshaft in order to increase the engine shaft work.
Date:
December 1945
Creator:
Hannum, Richard W.
System:
The UNT Digital Library
The Handley Page Type 42 Commercial Airplane (British): A Metal Sesquiplane
Circular presenting a description of the Handley Page 42, which is an all-metal sesquiplane. Details are provided of the cockpit, wings, fuselage, tail, power plant, landing gear, controls, and flying qualities.
Date:
December 1930
Creator:
unknown
System:
The UNT Digital Library
Wall interference in a two-dimensional-flow wind tunnel with consideration of the effect of compressibility
Report presenting tunnel-wall corrections for an airfoil of finite thickness and camber in a two-dimensional-flow wind tunnel. The theory takes account of the effects of the wake of the airfoil and of the compressibility of the fluid and is based on the assumption that the chord of the airfoil is small in comparison with the height of the tunnel. The theoretical results are compared with the small amount of low-speed experimental data available and agreement is seen to be satisfactory, even for relatively large values of the chord-height ratio.
Date:
December 1944
Creator:
Allen, H. Julian & Vincenti, Walter G.
System:
The UNT Digital Library
The Calculation of Span Load Distributions of Swept-Back Wings
"Span load distributions of swept-back wings have been calculated. The method used was to replace the wing with a bound vortex at the quarter-chord line and to calculate the downwash due to the system of bound and trailing vortices to conform at the three-quarter-chord line to the slope of the flat-plate wing surface. Results are given for constant-chord and 5:1 tapered plan forms, for sweep-back angles of 0 degrees, 30 degrees, and 45 degrees, and for aspect ratios of 3, 6, and 9" (p. 1).
Date:
December 1941
Creator:
Mutterperl, William
System:
The UNT Digital Library
Riveting in Metal Airplane Construction Part 1 : Riveting Methods and Equipment in German Metal Airplane Construction
"Although all constructors in Germany use duralumin quite frequently, and prefer cold riveting exclusively for permanent (nondetachable) connections of individual structural components, their methods and equipment are very diversified. The differences are due to a great extent to the diversity of structural types and to the special shapes of the individual subassemblies. The results is that different manufacturers have developed totally different riveting methods, as well as entirely different working methods" (p. 1).
Date:
December 1930
Creator:
Pleines, Wilhelm
System:
The UNT Digital Library
Aviation Engines in the Endurance Contest
The contest for engines of great endurance had entries of 13 types by the following firms: Breguet, Farman, Fiat, Hispano-Suiza, Lorraine-Dietrich, Panhard-Levassor, Peugeot, Renault, and Salmson.
Date:
December 1924
Creator:
Lehr, G.
System:
The UNT Digital Library
Measuring Vibration and Torque With the Oscillograph
"The recent development of technical science demands maximum reliability of functioning, together with maximum utilization of construction materials. For this purpose we must know what stresses are produced during functioning. One cause of great stresses are mechanical vibrations and this report describes a method of using an oscilloscope to measure the stresses of rapidly changing phenomena" (p. 1).
Date:
December 1924
Creator:
Elsässer, R.
System:
The UNT Digital Library
Investigation of the Aerodynamic Characteristics of the NACA RM-10 Missile (With Fins) at a Mach Number of 1.62 in the Langley 9-Inch Supersonic Tunnel
Report presenting an investigation of a fin-stabilized scale model of the NACA RM-10 missile at a Mach number of 1.62. Measurements were made of the lift, drag, and pitching moment of the finned body over a range of angles of attack. Comparisons with the results from other testing facilities are also provided.
Date:
December 19, 1952
Creator:
Coletti, Donald E.
System:
The UNT Digital Library
The Boulton and Paul "Bugle" Airplane: Day Bomber
The Bugle is a twin engine tractor biplane. It features two Jupiter engines and oleo-pneumatic landing gear. Its maximum speed is 120 MPH.
Date:
December 1926
Creator:
unknown
System:
The UNT Digital Library
The Supermarine "Southampton" Seaplane: Observation or Bomber
Purchased for the British Air Ministry, the Southampton seaplane uses 2 Napier Lion engines and has a boat hull with outriggers mounted on the wings. It was designed as a military aircraft and can be easily converted to a bomber. A description of the design, flight characteristics, and photographs and blueprints are provided.
Date:
December 1926
Creator:
unknown
System:
The UNT Digital Library
Compressive Strength of 24S-T Aluminum-Alloy Flat Panels With Longitudinal Formed Hat-Section Stiffeners
"Results are presented for a part of a test program on 24S-T aluminum alloy flat compression panels with longitudinal formed hat-section stiffeners. This part of the program is concerned with panels in which the thickness of the stiffener materials is 0.625 times the skin thickness. The results, presented in tabular and graphical form, show the effect of the relative dimensions of the panel on the buckling stress and the average stress at maximum load" (p. 1).
Date:
December 1946
Creator:
Schuette, Evan H.; Barab, Saul & McCracken, Howard L.
System:
The UNT Digital Library
An analysis of the airspeeds and normal accelerations of Boeing B-247 and B-247D airplanes in commercial transport operation
From Introduction: "The results of analyses of V-G data given in references 1 to 5 have shown that the flight loads of airplanes operated in commercial transport service are influenced by operating speeds and by forecasting and dispatching practices as reflected in differences between operations during the prewar and wartime periods. The available data are summarized and the flight results are compared with the results of analyses made in references 1 to 5."
Date:
December 1948
Creator:
Walker, Walter G. & Hadlock, Ivan K.
System:
The UNT Digital Library
Recommendations for numerical solution of reinforced-panel and fuselage-ring problems
Report presenting procedures for solving the equations of equilibrium of reinforced panels and isolated fuselage rings as represented by the external loads and operations table established according to Southwell's method. By using these equations, the stress distribution can be easily determined.
Date:
December 1948
Creator:
Hoff, N. J. & Libby, Paul A.
System:
The UNT Digital Library