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  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
 Year: 1943
 Collection: Technical Report Archive and Image Library
The advantages of uniform fuel distribution for air-cooled engines from considerations of cooling requirements and fuel economy

The advantages of uniform fuel distribution for air-cooled engines from considerations of cooling requirements and fuel economy

Date: December 1, 1943
Creator: Nielson, Jack
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Bearing strengths of bare and alclad XA75S-T and 24S-T81 aluminum alloy sheet

Bearing strengths of bare and alclad XA75S-T and 24S-T81 aluminum alloy sheet

Date: December 1, 1943
Creator: Moore, R L & Wescoat, C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A comparison at high speed of the aerodynamic merits of models of medium bombers having thickened wing roots and having wings with nacelles

A comparison at high speed of the aerodynamic merits of models of medium bombers having thickened wing roots and having wings with nacelles

Date: December 1, 1943
Creator: Draley, Eugene C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Construction of wire strain gages for engine application

Construction of wire strain gages for engine application

Date: December 1, 1943
Creator: Tucker, Maurice
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Correlation of single-cylinder cooling tests of a Pratt and Whitney R-2800-21 engine cylinder with wind-tunnel tests of a Pratt and Whitney R-2800-27 engine

Correlation of single-cylinder cooling tests of a Pratt and Whitney R-2800-21 engine cylinder with wind-tunnel tests of a Pratt and Whitney R-2800-27 engine

Date: December 1, 1943
Creator: Rollin, Vern G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Coupling of Flexural Propeller Vibrations with the Torsional Crankshaft Vibrations

The Coupling of Flexural Propeller Vibrations with the Torsional Crankshaft Vibrations

Date: December 1, 1943
Creator: Meyer, J.
Description: The exact mathematical treatment of the problem is possible by replacing the propeller blade by a homogeneous prismatic rod. Conclusions can them be drawn as to the behavior of an actual propeller, since tests on propeller blades have indicated a qualitative agreement with the homogeneous rod. The natural frequencies are determined and the stressing of the systems under the various vibration modes are discussed.
Contributing Partner: UNT Libraries Government Documents Department
Determination of the Mass Moments and Radii of Inertia of the Sections of a Tapered Wing and the Center-of-Gravity Line along the Wing Span

Determination of the Mass Moments and Radii of Inertia of the Sections of a Tapered Wing and the Center-of-Gravity Line along the Wing Span

Date: December 1, 1943
Creator: Savelyev, V. V.
Description: For computing the critical flutter velocity of a wing among the data required are the position of the line of centers of gravity of the wing sections along the span and the mass moments and radii of inertia of any section of the wing about the axis passing through the center of gravity of the section. A sufficiently detailed computation of these magnitudes even if the weights of all the wing elements are known, requires a great deal of time expenditure. Thus a rapid competent worker would require from 70 to 100 hours for the preceding computations for one wing only, while hundreds of hours would be required if all the weights were included. With the aid of the formulas derived in the present paper, the preceding work can be performed with a degree of accuracy sufficient for practical purposes in from one to two hours, the only required data being the geometric dimensions of the outer wing (tapered part), the position of its longerons, the total weight of the outer wing, and the approximate weight of the longerons, The entire material presented in this paper is applicable mainly to wings of longeron construction of the CAHI type and investigations ...
Contributing Partner: UNT Libraries Government Documents Department
The effect of surface finish on the fatigue performance of certain propeller materials

The effect of surface finish on the fatigue performance of certain propeller materials

Date: December 1, 1943
Creator: Russell, H W; Gillett, H W; Jackson, L R & Foley, G M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Fatigue strength and related characteristics of spot-welded joints in 24S-T alclad sheet

Fatigue strength and related characteristics of spot-welded joints in 24S-T alclad sheet

Date: December 1, 1943
Creator: Russell, H. W.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight tests of beveled-trailing-edge ailerons with various modifications on a North American XP-51 airplane (AAF No.41-38)

Flight tests of beveled-trailing-edge ailerons with various modifications on a North American XP-51 airplane (AAF No.41-38)

Date: December 1, 1943
Creator: Hoover, Herbert H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight tests of F2A-2 airplane with full-span slotted flaps and trailing-edge and slot-lip ailerons

Flight tests of F2A-2 airplane with full-span slotted flaps and trailing-edge and slot-lip ailerons

Date: December 1, 1943
Creator: Sawyer, Richard H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight Tests of Various Tail Modifications on the Brewster XSBA-1 Airplane II : Measurements of Flying Qualities with Tail Configuration Number Two

Flight Tests of Various Tail Modifications on the Brewster XSBA-1 Airplane II : Measurements of Flying Qualities with Tail Configuration Number Two

Date: December 1, 1943
Creator: Phillips, W.H. & Crane, H.L.
Description: Several tail modifications of the Brewster XSBA-1 scout-bomber were investigated and results compared. Modifications consisted of variation of the chord of the elevator and rudder while the total area of the surfaces is kept constant and variations of the total area of the vertical tail surface. Configuration number 2 reduced trim changes by 50 percent and reduced average elevator control force gradient from 30 to 27 pounds/g. Stick travel required to stall in maneuver was 4.6 inches.
Contributing Partner: UNT Libraries Government Documents Department
Grounding Electrical Equipment In and About Coal Mines

Grounding Electrical Equipment In and About Coal Mines

Date: December 1943
Creator: Griffith, Franklin E. & Gleim, E. J.
Description: Report issued by the U.S. Bureau of Mines on the safety measures used in keeping mining equipment grounded. Methods and instrumentation used in testing grounding equipment are presented. This report includes tables, and illustrations.
Contributing Partner: UNT Libraries Government Documents Department
Heat Transfer and Hydraulic Flow Resistance for Streams of High Velocity

Heat Transfer and Hydraulic Flow Resistance for Streams of High Velocity

Date: December 1, 1943
Creator: Lelchuk, V. L.
Description: Problems of hydraulic flow resistance and heat transfer for streams with velocities comparable with acoustic have present great importance for various fields of technical science. Especially, they have great importance for the field of heat transfer in designing and constructing boilers.of the "Velox" type. In this article a description of experiments and their results as regards definition of the laws of heat transfer in differential form for high velocity air streams inside smooth tubes are given.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of flow in an axially symmetrical heated jet of air

Investigation of flow in an axially symmetrical heated jet of air

Date: December 1, 1943
Creator: Corrsin, Stanley
Description: The work done under this contract falls essentially into two parts: the first part was the design and construction of the equipment and the running of preliminary tests on the 3-inch jet, carried out by Mr. Carl Thiele in 1940; the second part consisting in the measurement in the 1-inch jet flow in an axially symmetrical heated jet of air. (author).
Contributing Partner: UNT Libraries Government Documents Department
Limitations of lifting-line theory for estimation of aileron hinge-moment characteristics

Limitations of lifting-line theory for estimation of aileron hinge-moment characteristics

Date: December 1, 1943
Creator: Gillis, Clarence L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Measurements in flight of the stability, lateral control, and stalling characteristics of an airplane equipped with full-span Zap flaps and spoiler-type ailerons

Measurements in flight of the stability, lateral control, and stalling characteristics of an airplane equipped with full-span Zap flaps and spoiler-type ailerons

Date: December 1, 1943
Creator: Christophersen, Don R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Methods and charts for computing stability derivatives of a v-bottom planing surface

Methods and charts for computing stability derivatives of a v-bottom planing surface

Date: December 1, 1943
Creator: Freihofner, Anton
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Operating Temperatures of a Sodium-Cooled Exhaust Valve as Measured by a Thermocouple

Operating Temperatures of a Sodium-Cooled Exhaust Valve as Measured by a Thermocouple

Date: December 1, 1943
Creator: Sanders, J. C.; Wilsted, H. D. & Mulcahy, B. A.
Description: A thermocouple was installed in the crown of a sodium-cooled exhaust valve. The valve was then tested in an air-cooled engine cylinder and valve temperatures under various engine operating conditions were determined. A temperature of 1337 F was observed at a fuel-air ratio of 0.064, a brake mean effective pressure of 179 pounds per square inch, and an engine speed of 2000 rpm. Fuel-air ratio was found to have a large influence on valve temperature, but cooling-air pressure and variation in spark advance had little effect. An increase in engine power by change of speed or mean effective pressure increased the valve temperature. It was found that the temperature of the rear spark-plug bushing was not a satisfactory indication of the temperature of the exhaust valve.
Contributing Partner: UNT Libraries Government Documents Department
Piston Ring Pressure Distribution

Piston Ring Pressure Distribution

Date: December 1, 1943
Creator: Kuhn, M.
Description: The discovery and introduction of the internal combustion engine has resulted in a very rapid development in machines utilizing the action of a piston. Design has been limited by the internal components of the engine, which has been subjected to ever increasing thermal and mechanical stresses, Of these internal engine components, the piston and piston rings are of particular importance and the momentary position of engine development is not seldom dependent upon the development of both of the components, The piston ring is a well-known component and has been used in its present shape in the steam engine of the last century, Corresponding to its importance, the piston ring has been a rich field for creative activity and it is noteworthy that in spite of this the ring has maintained its shape through the many years. From the many and complicated designs which have been suggested as a packing between piston and cylinder wall hardly one suggestion has remained which does not resemble the original design of cast iron rectangular ring.
Contributing Partner: UNT Libraries Government Documents Department
Preliminary aerodynamic and structural tests showing the effect of compressive load on the fairness of a low-drag wing specimen with chordwise hat-section stiffeners

Preliminary aerodynamic and structural tests showing the effect of compressive load on the fairness of a low-drag wing specimen with chordwise hat-section stiffeners

Date: December 1, 1943
Creator: Rossman, Carl A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A preliminary study of machine-countersunk flush rivets subjected to a combined static and alternating shear load

A preliminary study of machine-countersunk flush rivets subjected to a combined static and alternating shear load

Date: December 1, 1943
Creator: Crate, Harold
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Propellers in yaw

Propellers in yaw

Date: December 1, 1943
Creator: Ribner, Herbert S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Proposal for a propeller side-force factor

Proposal for a propeller side-force factor

Date: December 1, 1943
Creator: Ribner, Herbert S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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