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Creep of 2S-O Aluminum Sheet at 500 and 550 C

Description: Abstract: "Creep and creep-rupture tests were made on 25-O aluminum sheet at temperatures of 500 and 550 C. The estimated stresses that will produce 0.5 per cent deformation and rupture in 10,000 hours at 400, 450, 500, and 550 C (data at 400 and 450 C are from BMI-T-29, dated June 9, 1950) are presented."
Date: September 11, 1952
Creator: VanEcho, J. A.; Simmons, W. F. & Cross, H. C.
Partner: UNT Libraries Government Documents Department

An Exploration of the Longitudinal Tensile and Compressive Properties Throughout an Extruded Shape of 24S-T Aluminum Alloy

Description: Note presenting an investigation of tensile and compressive properties of specimens cut from an extruded shape of 24S-T aluminum alloy. The tensile strengths, tensile yield strengths, elongations, and compressive yield strengths of both the uncrystallized and recrystallized portions were determined. The strength of a cross section of an extruded shape is the weighted average of the strengths of the unrecrystallized and the recrystallized areas.
Date: December 1942
Creator: Paul, D. A.
Partner: UNT Libraries Government Documents Department

Nondestructive Test Methods for Spot Welds in Aluminum Alloys

Description: Note presenting the results of a study and research investigation of nondestructive test methods for spot welds in aluminum-alloy sheets. The purpose of the research was to investigate proposed nondestructive test methods for spot welds in aluminum alloys, to determine the feasibility of the tests, and to recommend the research methods found suitable for development and reduction to practical application.
Date: November 1944
Creator: McMaster, R. C.; Manildi, J. F. & Woolsey, C. C.
Partner: UNT Libraries Government Documents Department

Procedure Used at Aluminum Research Laboratories for Determining Type of Attack in Some Aluminum Alloys

Description: Report presenting samples of 17S-T and 24S-T aluminum alloys subjected to accelerated corrosion tests in which the corrosion period was established at 6 hours for samples that had been etched to produce a uniform surface. The results indicate the types of corrosion attack, which are described in standard terminology, and may form a basis for estimating the resistance of the material to corrosion by a comparison of the relative depth and frequency of the corrosive attacks.
Date: August 1942
Creator: Walton, C. J. & Keller, F.
Partner: UNT Libraries Government Documents Department

Internal-Friction Study of Aluminum Alloy Containing 4 Weight Percent Copper

Description: Note presenting a study of aluminum alloy containing 4 weight percent copper during aging using low-frequency internal-friction measurements in torsional and flexural vibration. Both polycrystalline and single-crystal specimens exhibit an initial internal-friction peak at 173 degrees Celsius after solution treatment and quenching.
Date: August 1958
Creator: Berry, B. S. & Nowick, A. S.
Partner: UNT Libraries Government Documents Department

Biaxial Fatigue Strength of 24S-T Aluminum Alloy

Description: Note presenting an investigation to determine the fatigue-strength values for 24S-T aluminum alloy when subjected to various ratios of biaxial stresses. The stresses considered were both tensile. The results indicated that uniaxial fatigue-strength values in the longitudinal direction cannot be used to predict the fatigue strength, and that biaxial fatigue strength may be as low as 50 percent of the uniaxial fatigue strength.
Date: May 1949
Creator: Marin, Joseph & Shelson, William
Partner: UNT Libraries Government Documents Department

Biaxial Plastic Stress-Strain Relations for 24S-T Aluminum Alloy

Description: Note presenting an investigation to determine the yield strength, ultimate strength, ductility, and plastic stress-stain relations for 24S-T aluminum alloy when subjected to biaxial stresses. The data were interpreted by a generalized St. Venant theory in an attempt to predict the biaxial stress-strain relations in terms of the uniaxial tensile stress-strain relations. Stress-strain data were also obtained from flat control specimens cut from tubular specimens and compared with tension test data obtained from tubular specimens.
Date: May 1948
Creator: Marin, Joseph; Faupel, J. H.; Dutton, V. L. & Brossman, M. W.
Partner: UNT Libraries Government Documents Department

Interface Thermal Conductance of Twenty-Seven Riveted Aircraft Joints

Description: Note presenting testing of twenty-seven structural joint specimens of 2024-T3 and 2024-T4 aluminum alloy consisting of a T-stringer riveted to a 10- by 10-inch skin surface under simulated aerodynamic heating with no external loading applied. Rivet size and pitch were found to influence the conductance but the rivet materials tested had no observable effect.
Date: July 1957
Creator: Barzelay, Martin E. & Holloway, George F.
Partner: UNT Libraries Government Documents Department

Investigation of the Validity of an Ideal Theory of Elasto-Plasticity for Wrought Aluminum Alloys

Description: Note presenting an investigation to determine the relation between stresses and plastic strains of wrought aluminum alloys for three types of loading: tension, compression, and torsion. A secondary objective was to identify which assumptions of an ideal theory of elasto-plasticity are invalid for the alloys. Universal stress-strain curves as predicted by the theory were not obtained with wrought aluminum alloys.
Date: July 1948
Creator: Thomsen, E. G.; Cornet, I.; Lotze, I. & Dorn, J. E.
Partner: UNT Libraries Government Documents Department

Comparison of Fatigue Strengths of Bare and Alclad 24S-T3 Aluminum-Alloy Sheet Specimens Tested at 12 and 1000 Cycles Per Minute

Description: Note presenting the results of axial fatigue tests conducted on 0.032-inch-thick flat-sheet specimens of bare and alclad 24S-T3 aluminum alloy to determine the effect of frequency of loading on the fatigue strengths of these materials. The number of cycles to failure varied from about 150 to over 10,000,000 and tests were conducted using completely reversed axial load at two frequencies of loading.
Date: December 1950
Creator: Smith, Frank C.; Brueggeman, William C. & Harwell, Richard H.
Partner: UNT Libraries Government Documents Department

The Shear of Aluminum Alloy Driven Rivets as Affected by Increasing D/T Ratios

Description: "A decrease in shear strengths for increasing D/t ratios was shown in a previous investigation of protruding-head aluminum alloy rivets in double shear conducted at Aluminum Research Laboratories in 1942. Since single shear joints are more common than double shear joints, it was desirable to extend the investigation to single shear joints. This reports describes the results of this investigation of single shear joints and also includes the results of the previous investigation on double shear joints" (p. 1).
Date: July 1944
Creator: Hartman, E. C. & Wescoat, C.
Partner: UNT Libraries Government Documents Department

The Column Strength of Two Extruded Aluminum-Alloy H-Sections

Description: "Extruded aluminum-alloy members of various cross sections are used in aircraft as compression members either singly or as stiffeners for aluminum-alloy sheet. In order to design such members, it is necessary to know their column strength or, in the case of stiffeners, the value of the double modulus, which is best obtained for practical purposes from column tests. Column tests made on two extruded h-sections are described, and column formulas and formulas for the ratio of the double modulus to Young's modulus, based on the tests, are given" (p. 289).
Date: September 30, 1938
Creator: Osgood, William R. & Holt, Marshall
Partner: UNT Libraries Government Documents Department

Column and Plate Compressive Strengths of Aircraft Structural Materials: Extruded R303-T Aluminum Alloy

Description: "Column and plate compressive strengths of extruded R303-T aluminum alloy were determined both within and beyond the elastic range form tests of thin-strip columns and local-instability tests of H-, Z-, and channel-section columns. These tests are part of an extensive research investigation to provide data on the structural strength of various aircraft materials. The results are presented in the form of curves and charts that are suitable for use in the design and analysis of aircraft structures" (p. 1).
Date: October 1945
Creator: Heimerl, George J. & Fay, Douglas P.
Partner: UNT Libraries Government Documents Department

Cumulative Fatigue Damage of Axially Loaded Alclad 75S-T6 and Alclad 24S-T3 Aluminum-Alloy Sheet

Description: Note presenting the results of cumulative-fatigue-damage tests made on 607 specimens machined from alclad 75S-T6 aluminum-alloy sheet 0.064 inch thick and 198 specimens of alclad 24S-T3 and alclad 75S-T6 aluminum-alloy sheet 0.032 inch thick. The cumulative-damage ratio was calculated as the sum of the ratios of the numbers of cycles applied at the different stress levels to the number of cycles at the same stress level that would cause failure.
Date: September 1955
Creator: Smith, Ira; Howard, Darnley M. & Smith, Frank C.
Partner: UNT Libraries Government Documents Department

Effect of Service Stress on Impact Resistance, X-Ray Diffraction Patterns, and Microstructure of 25S Aluminum Alloy

Description: Report presents the results of a great number of tests made to determine the effect of service stresses on the impact resistance, the x-ray diffraction patterns, and the microstructure of 25s aluminum alloy. Many of the specimens were taken from actual propeller blades and others were cut from 13/16-inch rod furnished by the Aluminum Company of America.
Date: 1939
Creator: Kies, J. A. & Quick, G. W.
Partner: UNT Libraries Government Documents Department

Improvement of Fatigue Life of an Aluminum Alloy by Overstressing

Description: "Fatigue tests were made on some 1.375-inch-diameter and 0.300-inch diameter specimens of a 17S-T aluminum alloy rod. One test of a large specimen was run continuously to failure at a maximum stress of 22,000 pounds per square inch. In two other tests of large specimens, thin surface layers were removed periodically until failure occurred. The same nominal maximum stress of 22,000 pounds per square inch was used throughout the two tests and the load on the fatigue machine was lowered accordingly after the removal of each surface layer" (p. 1).
Date: August 1942
Creator: Stickley, G. W.
Partner: UNT Libraries Government Documents Department

Fatigue Strength and Related Characteristics of Aircraft Joints 1: Comparison of Spot-Weld and Rivet Patterns in 24S-T Alclad and 75S-T Alclad

Description: Report contains detailed results of a number of fatigue tests on spot-welded joints in aluminum alloys. The tests described include: (1) fatigue tests on spot-welded lap joints in sheets of unequal thickness of alclad 24s-t. These tests indicate that the fatigue strength of a spot-welded joint in sheets of two different gages is slightly higher than that of a similar joint in two sheets of the thinner gage but definitely lower than that of a similar joint in two sheets of the thicker gage. (2) Fatigue tests on spot-welded alclad 75s-t spot-welded lap-joint specimens of alclad 75s-t were not any stronger in fatigue than similar specimens of alclad 24s-t. (3) Fatigue tests on lap-joint specimens spot -welded after various surface preparations--these included ac welding wire-brushed surfaces, dc welding wire-brushed surfaces, and dc welding chemically cleaned surfaces. While the ac welds were strongest statically, the dc welds on wire-brushed surfaces were strongest in fatigue. Specimens prepared in this way were very nearly as strong as the best riveted specimens tested for comparison. (4) Fatigue tests on specimens spot-welded with varying voltage so as to include a wide range of static spot-weld strengths. The fatigue strengths were in the same order as the static strengths but showed less range. (author).
Date: December 1944
Creator: Russell, H. W.; Jackson, L. R.; Grover, H. J. & Beaver, W. W.
Partner: UNT Libraries Government Documents Department

Effect of Alternately High and Low Repeated Stresses Upon the Fatigue Strength of 25S-T Aluminum Alloy

Description: "Fatigue tests were made on one lot of 3/4 inch diameter rolled-and-drawn 25S-T aluminum-alloy rod normal in composition and tensile properties. The specimens were tested at 3500 cycles per second in a rotating-beam fatigue test machine. Tests were made for three ratios (20:1, 50:1, and 200:1) of the number of cycles applied at low stress to the number applied at high stress. In general, failure occurred when the number of cycles at either the low or the high stress approached the ordinary fatigue curve for the material, regardless of the sequence in which the stresses were applied" (p. 1).
Date: January 1941
Creator: Stickley, G. W.
Partner: UNT Libraries Government Documents Department

Combined-Stress Fatigue Strength of 76S-T61 Aluminum Alloy With Superimposed Mean Stresses and Corrections for Yielding

Description: Note presenting fatigue data for 76S-T61 aluminum alloy for several combinations of bending and torsion with both alternating and mean stresses. The literature on the effect of combined stress and of mean stress in fatigue is reviewed and the results of the present series are compared with those of various theories. Results regarding fatigue data, fatigue fractures, and static tests are provided.
Date: May 1953
Creator: Findley, William N.
Partner: UNT Libraries Government Documents Department

The Effect of Methods of Testing on the Ultimate Loads Supported by Stiffened Flat Sheet Panels Under Edge Compression

Description: Note presenting testing of two series of stiffened flat sheet specimens tested under edge compression using various end conditions: round ends, flat ends, and continuous panels. The specimens consisted of aluminum-alloy flat sheet stiffened by three hat-shaped extruded aluminum-alloy stiffeners. The results indicated that the length of the specimen has an insignificant effect on the ultimate compressive load.
Date: June 1941
Creator: Holt, Marshall
Partner: UNT Libraries Government Documents Department

The Effect of Preheating and Postheating on the Quality of Spot Welds in Aluminum Alloys

Description: Note presenting an investigation to determine the effect of preheating and postheating cycles on the quality and strength of spot welds in aluminum alloys. The results showed that the combination of a slowly rising condenser-discharge preheat current with a rapidly rising welding current afforded no more freedom from expulsion than was obtained with the rapidly rising welding current alone.
Date: November 1947
Creator: Hess, W. F.; Wyant, R. A. & Winsor, F. J.
Partner: UNT Libraries Government Documents Department

Fatigue Tests on Notched and Unnotched Sheet Specimens of 2024-T3 and 7075-T6 Aluminum Alloys and of SAE 4130 Steel With Special Consideration of the Life Range From 2 to 10,000 Cycles

Description: Note presenting fatigue tests performed on notched and unnotched sheet specimens made of 2024-T3 and 7075-T6 aluminum alloys and of SAE 4130 steel. The steel was tested in two conditions: normalized and heat-treated to a tensile strength of 180 ksi. The primary focus was on the life range from 2 to 10,000 cycles.
Date: December 1956
Creator: Illg, Walter
Partner: UNT Libraries Government Documents Department