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Determination of plate compressive strengths

Description: From Summary: "Results of local-instability tests of H-, Z-, and C-section plate assemblies of four extruded aluminum alloys and two magnesium alloys, obtained in an extensive investigation to determine plate compressive strengths of aircraft structural materials, are summarized. On the basis of the general relationships found between the plate compressive strengths and the compressive stress-strain curves, methods applicable to flat plates and based upon the use of the compressive stress-strain curve are suggested for determining the critical compressive stress and the average stress at maximum load."
Date: December 1947
Creator: Heimerl, George J.
Partner: UNT Libraries Government Documents Department

Methods of constructing charts for adjusting test results for the compressive strength of plates for differences in material properties

Description: "Methods are presented for constructing charts suitable for adjusting to standard values plate test results for the critical compressive stress and the average stress at maximum load. The methods take into account the difference between the compressive properties of the material used for the tests and those upon which the design is to be based. Illustrative charts are included for extruded 24S-T and 75S-T aluminum alloys" (p. 1).
Date: April 1948
Creator: Heimerl, George J.
Partner: UNT Libraries Government Documents Department

Time-temperature parameters and an application to rupture and creep of aluminum alloys

Description: Report presenting the application of time-temperature parameters to stress-strain, rupture, and creep data for metals and alloys. A parameter based on rate-process theory was successfully applied to rupture and creep data for aluminum and various aluminum alloys.
Date: June 1954
Creator: Heimerl, George J.
Partner: UNT Libraries Government Documents Department

Determination of plate compressive strengths at elevated temperatures

Description: From Summary: "The results of local-instability tests of H-section plate assemblies and compressive stress-strain tests of extruded 75S-T6 aluminum alloy, obtained to determine flat-plate compressive strengths under stabilized elevated-temperature conditions, are given for temperatures up to 600 degrees Fahrenheit. The results show that methods available for calculating the critical compressive stress at room temperature can also be used at elevated temperatures if the applicable compressive stress-strain curve for the material is given."
Date: February 1949
Creator: Heimerl, George J. & Roberts, William M.
Partner: UNT Libraries Government Documents Department

Determination of desirable lengths of Z- and channel-section columns for local-instability tests

Description: From Summary: "Local-instability tests of 24S-T aluminum-alloy formed Z- and channel-section columns were made in order to determine a length of test specimen that would avoid the increased strength associated with short lengths and also permit the occurrence of a convenient buckling pattern. The effect of column length on the critical compressive stress, on the average stress at maximum load, and on the number of half-waves of the buckling pattern is shown."
Date: October 1944
Creator: Heimerl, George J. & Roy, J. Albert
Partner: UNT Libraries Government Documents Department

Determination of plate compressive strengths at elevated temperatures

Description: The results of local-instability tests of h-section plate assemblies and compressive stress-strain tests of extruded 75s-t6 aluminum alloy, obtained to determine flat-plate compressive strength under stabilized elevated temperature conditions, are given for temperatures up to 600 degrees F. The results show that methods available for calculating the critical compressive stress at room temperature can also be used at elevated temperatures if the applicable compressive stress-strain curve for the material is given.
Date: 1950
Creator: Heimerl, George J. & Roberts, William M.
Partner: UNT Libraries Government Documents Department

Column and Plate Compressive Strengths of Aircraft Structural Materials: Extruded 24S-T Aluminum Alloy

Description: Column and plate compressive strengths of extruded 24S-T aluminum alloy were determined both within and beyond the elastic range from 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.
Date: July 1945
Creator: Heimerl, George J. & Roy, J. Albert
Partner: UNT Libraries Government Documents Department

Generalized master curves for creep and rupture

Description: Report presenting the similarity of Larson-Miller master curves for rupture life and minimum creep rate for aluminum, two aluminum alloys, two steels, and two high-temperature high-strength alloys. The approximate invariance of the product of rupture life and minimum creep rate is also shown for these materials.
Date: October 1957
Creator: Heimerl, George J. & McEvily, Arthur J., Jr.
Partner: UNT Libraries Government Documents Department

Column and plate compressive strengths of aircraft structural materials: Extruded 0-1HTA magnesium alloy

Description: Column and plate compressive strengths of extruded 0-1HTA magnesium alloy were determined both within and beyond the elastic range from tests of flat end H-section columns and from 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.
Date: January 1947
Creator: Heimerl, George J. & Niles, Donald E.
Partner: UNT Libraries Government Documents Department

Column and plate compressive strengths of aircraft structural materials: 17S-T aluminum-alloy sheet

Description: From Summary: "Column and plate compressive strengths of 17S-T aluminum-alloy sheet were determined both within and beyond the elastic range from tests of thin-strip columns and from local-instability tests of formed Z- and channel-section columns. These tests are part of an extensive research investigation to provide data on the structural strengths of various aircraft materials. Results are presented in the form of curves and charts that may be used in the design and analysis of aircraft structures."
Date: June 1945
Creator: Heimerl, George J. & Roy, J. Albert
Partner: UNT Libraries Government Documents Department

Column and plate compressive strengths of aircraft structural materials: Extruded 14S-T aluminum alloy

Description: From Summary: "Column and plate compressive strengths of extruded 14S-T aluminum alloy were determined both within and beyond the elastic range from tests of flat-end H-section columns and from 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."
Date: May 1946
Creator: Heimerl, George J. & Niles, Donald E.
Partner: UNT Libraries Government Documents Department

Column and plate compressive strengths of aircraft structural materials: extruded 75S-T aluminum alloy

Description: Report presenting column and plate compressive strengths of extruded 75S-T aluminum alloy both within and beyond the elastic range from tests of thin-strip columns and local-instability tests of H-, Z-, and channel-section columns. The tests are part of an extensive research investigation to provide data on the structural strength of various aircraft materials. Results regarding compressive stress-strain curves and column and plate compressive strengths are provided.
Date: July 1945
Creator: Heimerl, George J. & Roy, J. Albert
Partner: UNT Libraries Government Documents Department

Column and plate compressive strengths of aircraft structural materials: extruded 24S-T aluminum alloy

Description: Report presenting column and plate compressive strengths of extruded 24S-T aluminum alloy determined both within and beyond the elastic range from tests of thin-strip columns and local-instability tests of H-, Z-, and channel-section columns. The tests are part of a research investigation to provide data on the structural strength of various aircraft materials. Results regarding compressive stress-strain curves and column and plate compressive strengths are provided.
Date: July 1945
Creator: Heimerl, George J. & Roy, J. Albert
Partner: UNT Libraries Government Documents Department

Increasing the compressive strength of 24S-T aluminum-alloy sheet by flexure rolling

Description: From Summary: "A method of increasing the compressive strength of 24S-T aluminum-alloy sheet by flexure rolling was investigated. In this method, the sheet was alternately bent and then straightened by rolling a four-step procedure. The results showed that the greatest increase was in compressive yield stress in the with-grain direction regardless of the direction of rolling; the increase was greater as the radius of flexure rolling became smaller and as the number of steps was increased. The tensile properties, however, were little affected."
Date: August 1946
Creator: Heimerl, George J. & Woods, Walter
Partner: UNT Libraries Government Documents Department

Structural efficiencies of various aluminum, titanium, and steel alloys at elevated temperatures

Description: Efficient temperature ranges are indicated for two high-strength aluminum alloys, two titanium alloys, and three steels for some short-time compression-loading applications at elevated temperatures. Only the effects of constant temperatures and short exposure to temperature are considered, and creep is assumed not to be a factor. The structural efficiency analysis is based upon preliminary results of short-time elevated-temperature compressive stress-strain tests of the materials. The analysis covers strength under uniaxial compression, elastic stiffness, column buckling, and the buckling of long plates in compression or in shear.
Date: July 1953
Creator: Heimerl, George J. & Hughes, Philip J.
Partner: UNT Libraries Government Documents Department

Effect of brake forming in various tempers on the strength of Alclad 75S-T aluminum-alloy sheet

Description: Results are presented of tests to determine the effect of brake forming in various tempers on the strength of Alclad 75S-T aluminum alloy sheet in the direction parallel to the brake. The tensile and compressive strengths of Alclad 75S-T sheet, formed in the O and W tempers, were either increased or little affected compared with those of similarly treated unformed material. When Alclad 75S-T sheet 'as received' was formed, however, the tensile yield stress was reduced about 7 percent for the with-grain direction and 1 percent for the cross-grain direction, whereas the tensile ultimate and compressive yield stresses were increased somewhat. The elongation was always slightly reduced as a result of forming.
Date: January 1947
Creator: Woods, Walter & Heimerl, George J.
Partner: UNT Libraries Government Documents Department

Effect of brake forming on the strength of 24S-T aluminum-alloy sheet

Description: Tests were made to determine the effect of brake forming on the strength of 24S-T aluminum alloy sheet that had been formed to an inside bend radius of three times the sheet thickness. The results for both directions of the grain of the material showed that the compressive yield stresses were appreciably increased, that the tensile yield stresses were moderately increased, that the ultimate tensile stresses were only slightly increased, that the elongations were considerably reduced, and that the shapes of the tensile and compressive stress-strain curves were markedly changed.
Date: May 1946
Creator: Heimerl, George J. & Woods, Walter
Partner: UNT Libraries Government Documents Department

Tensile properties of 7075-T6 and 2024-T3 aluminum-alloy sheet heated at uniform temperature rates under constant load

Description: Results are presented of tests to determine the effect of heating at uniform temperature rates from 0.2 degrees to 100 degrees F per second on the tensile properties of 7075-T6 d(75s-T6) and 2024-T3 (24s-T3) aluminum-alloy sheet under constant-load conditions. Yield and rupture stresses, obtained under rapid-heating conditions, are compared with results of elevated-temperature stress-strain tests for 1/2-hour exposure. Master yield-and-rupture-stress curves based on linear temperature-rate parameter are presented. Yield and rupture stresses and temperatures may be predicted by means of master curves and the parameter.
Date: July 1955
Creator: Heimerl, George J. & Inge, John E.
Partner: UNT Libraries Government Documents Department

Plastic buckling of simply supported compressed plates

Description: Report presenting an investigation to ascertain the validity of various theories for the plastic buckling of compressed simply supported plates by means of local-instability tests of drawn square tubes of 14S-T6 aluminum alloy. The results obtained were in excellent agreement with Stowell's unified theory for the plastic buckling of columns and plates.
Date: April 1949
Creator: Pride, Richard A. & Heimerl, George J.
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

Column and plate compressive strengths of aircraft structural materials: 24S-T aluminum-alloy sheet

Description: From Summary: "Column and plate compressive strengths of 24S-T aluminum-alloy sheet were determined both within and beyond the elastic range from tests of thin-strip columns and from local-instability tests of formed Z-end channel-section columns. These tests are the first of a series in an extensive research investigation to provide data on the structural strength of various aircraft materials. The results, which are presented in the form of curves and charts that may be used in the design and analysis of aircraft structures, supersede preliminary results published previously."
Date: June 1945
Creator: Lundquist, Eugene E.; Schuette, Evan H.; Heimerl, George J. & Roy, J. Albert
Partner: UNT Libraries Government Documents Department

Charts for calculation of the critical stress for local instability of columns with I-, Z-, channel and rectangular-tube section

Description: Report presenting charts for the calculation of the critical stress for local instability of columns with I-, Z-, channel-, and rectangular-tube sections. An experimental curve is included for use in taking into account the effect of stresses above the elastic range on 24S-T aluminum alloy elasticity.
Date: November 1943
Creator: Kroll, W. D.; Fisher, Gordon P. & Heimerl, George J.
Partner: UNT Libraries Government Documents Department

Tensile properties of Inconel and RS-120 titanium-alloy sheet under rapid-heating and constant-temperature conditions

Description: From Summary: "Results are presented of rapid-heating tests to determine the tensile strength of Inconel and RS-120 titanium-alloy sheet heated to failure at uniform temperature rates from 0.2 degrees Fahrenheit to 100 degrees Fahrenheit per second under constant load conditions. Yield and rupture stresses, obtained by rapid heating, are compared with yield and ultimate stresses from elevated-temperature tensile stress-strain tests for 1/2-hour exposure. The applicability of master curves and temperature-rate parameters to the prediction of yield and rupture stresses and temperatures under rapid-heating conditions was investigated."
Date: July 1956
Creator: Heimerl, George J.; Kurg, Ivo M. & Inge, John E.
Partner: UNT Libraries Government Documents Department