Lundquist, Eugene E.
Overview
Works:  46 works in 103 publications in 1 language and 402 library holdings 

Roles:  Author, Contributor 
Publication Timeline
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Most widely held works by
Eugene E Lundquist
Strength tests of thinwalled duralumin cylinders in pure bending by
Eugene E Lundquist(
Book
)
3 editions published between 1933 and 1942 in English and held by 13 WorldCat member libraries worldwide
This report is the third of a series presenting the results of strength tests on thinwalled cylinders and truncated cones of circular and elliptic section; it includes the results obtained from pure bending tests on 58 thinwalled duralumin cylinders of circular section with ends clamped to rigid bulkheads. The tests show that the stress on the extreme fiber at failure as calculated by the ordinary theory of bending is from 30 to 80 percent greater than the compressive stress at failure for thinwalled cylinders in compression. The tests also showe that length/radius ratio has no consistent effect upon the bending strength and that the size of the wrinkles that form on the compression half of a cylinder in bending is approximately equal to the size of the wrinkles that form in the complete circumference of a cylinder of the same dimensions in compression
3 editions published between 1933 and 1942 in English and held by 13 WorldCat member libraries worldwide
This report is the third of a series presenting the results of strength tests on thinwalled cylinders and truncated cones of circular and elliptic section; it includes the results obtained from pure bending tests on 58 thinwalled duralumin cylinders of circular section with ends clamped to rigid bulkheads. The tests show that the stress on the extreme fiber at failure as calculated by the ordinary theory of bending is from 30 to 80 percent greater than the compressive stress at failure for thinwalled cylinders in compression. The tests also showe that length/radius ratio has no consistent effect upon the bending strength and that the size of the wrinkles that form on the compression half of a cylinder in bending is approximately equal to the size of the wrinkles that form in the complete circumference of a cylinder of the same dimensions in compression
The Pressure distribution over a square wing tip on a biplane in flight by
Richard V Rhode(
Book
)
2 editions published between 1930 and 1931 in English and held by 9 WorldCat member libraries worldwide
The results are given in tables and curves in such form that the load distribution for any lift coefficient within the usual range encountered in flight may be determined easily. They show that the shape of the lower tip has no influence on the load distribution over the upper tip and also that a simple end fairing on the square tip results in an appreciable reduction of tip load extending inboard a distance equal to about 40 percent of the chord length. The reduction in tip load is accompanied by a simultaneous forward shift of the center of pressure on the same part of the wing
2 editions published between 1930 and 1931 in English and held by 9 WorldCat member libraries worldwide
The results are given in tables and curves in such form that the load distribution for any lift coefficient within the usual range encountered in flight may be determined easily. They show that the shape of the lower tip has no influence on the load distribution over the upper tip and also that a simple end fairing on the square tip results in an appreciable reduction of tip load extending inboard a distance equal to about 40 percent of the chord length. The reduction in tip load is accompanied by a simultaneous forward shift of the center of pressure on the same part of the wing
The Pressure distribution over a semicircular wing tip on a biplane in flight by
Richard V Rhode(
Book
)
3 editions published in 1931 in English and held by 9 WorldCat member libraries worldwide
This note presents the results of flight pressure distribution tests on the right upper wing panel of a Douglas M3 airplane equipped with a semicircular wing tip
3 editions published in 1931 in English and held by 9 WorldCat member libraries worldwide
This note presents the results of flight pressure distribution tests on the right upper wing panel of a Douglas M3 airplane equipped with a semicircular wing tip
Principles of moment distribution applied to stability of structures composed of bars or plates by
Eugene E Lundquist(
Book
)
8 editions published between 1943 and 1945 in English and held by 9 WorldCat member libraries worldwide
The principles of the cross method of moment distribution, which have previously been applied to the stability of structures composed of bars under axial load, are applied to the stability of structures composed of long plates under longitudinal load. A brief theoretical treatment of the subject, as applied to structures composed of either bars or plates, is included, together with an illustrative example for each of these two types of structure. An appendix presents the derivation of the formulas for the various stiffnesses and carryover factors used in solving problems in the stability of structures composed of long plates
8 editions published between 1943 and 1945 in English and held by 9 WorldCat member libraries worldwide
The principles of the cross method of moment distribution, which have previously been applied to the stability of structures composed of bars under axial load, are applied to the stability of structures composed of long plates under longitudinal load. A brief theoretical treatment of the subject, as applied to structures composed of either bars or plates, is included, together with an illustrative example for each of these two types of structure. An appendix presents the derivation of the formulas for the various stiffnesses and carryover factors used in solving problems in the stability of structures composed of long plates
The Pressure distribution over a Douglas wing tip on a biplane in flight by
Richard V Rhode(
Book
)
2 editions published between 1930 and 1931 in English and held by 9 WorldCat member libraries worldwide
The results are given in tables and curves in such form that the load distribution for any conditions may be determined easily
2 editions published between 1930 and 1931 in English and held by 9 WorldCat member libraries worldwide
The results are given in tables and curves in such form that the load distribution for any conditions may be determined easily
Strength tests on paper cylinders in compression, bending, and shear by
Richard V Rhode(
Book
)
3 editions published in 1931 in English and held by 9 WorldCat member libraries worldwide
Static tests on paper cylinders were conducted to obtain qualitative information in connection with a study of the strength of stressedskin fuselages. The effects of radiusthickness ratio and bulkhead spacing were investigated with the cylinders in compression, bending, combined bending and shear, and torsion
3 editions published in 1931 in English and held by 9 WorldCat member libraries worldwide
Static tests on paper cylinders were conducted to obtain qualitative information in connection with a study of the strength of stressedskin fuselages. The effects of radiusthickness ratio and bulkhead spacing were investigated with the cylinders in compression, bending, combined bending and shear, and torsion
Preliminary study of applied load factors in bumpy air by
Richard V Rhode(
Book
)
3 editions published in 1931 in English and held by 8 WorldCat member libraries worldwide
Theoretical relations involved in the study are reviewed to furnish a basis upon which the experimental data can be properly analyzed. The structure of the atmosphere in relation to the loadfactor problem is briefly discussed, and the acceleration data obtained on a number of flights with various airplanes are presented and analyzed to the extent that the results are applicable to any airplane
3 editions published in 1931 in English and held by 8 WorldCat member libraries worldwide
Theoretical relations involved in the study are reviewed to furnish a basis upon which the experimental data can be properly analyzed. The structure of the atmosphere in relation to the loadfactor problem is briefly discussed, and the acceleration data obtained on a number of flights with various airplanes are presented and analyzed to the extent that the results are applicable to any airplane
Tables of stiffness and carryover factor for structural members under axial load by
Eugene E Lundquist(
Book
)
3 editions published in 1938 in English and held by 8 WorldCat member libraries worldwide
Tables of stiffness and carryover factor are presented for members in which the cross section and axial load do not vary along the length of the member. These tables are of use in solving problems in the stability of structural members under axial load as well as in applications of the Cross method of moment distribution when the effects of axial load in the members are considered. The interval between successive values of the argument is small enough to make interpolation unnecessary in engineering calculations
3 editions published in 1938 in English and held by 8 WorldCat member libraries worldwide
Tables of stiffness and carryover factor are presented for members in which the cross section and axial load do not vary along the length of the member. These tables are of use in solving problems in the stability of structural members under axial load as well as in applications of the Cross method of moment distribution when the effects of axial load in the members are considered. The interval between successive values of the argument is small enough to make interpolation unnecessary in engineering calculations
Generalized analysis of experimental observations in problems of elastic stability by
Eugene E Lundquist(
Book
)
4 editions published in 1938 in English and held by 8 WorldCat member libraries worldwide
A generalized method of analyzing experimental observations in problems of elastic stability is presented in which the initial readings of load and deflection may be taken at any load less than the critical load. This analysis is an extension of a method published by Southwell in 1932, in which it was assumed that the intial readings are taken at zero load
4 editions published in 1938 in English and held by 8 WorldCat member libraries worldwide
A generalized method of analyzing experimental observations in problems of elastic stability is presented in which the initial readings of load and deflection may be taken at any load less than the critical load. This analysis is an extension of a method published by Southwell in 1932, in which it was assumed that the intial readings are taken at zero load
Comparison of three methods for calculating the compressive strength of flat and slightly curved sheet and stiffner combinations by
Eugene E Lundquist(
Book
)
3 editions published in 1933 in English and held by 7 WorldCat member libraries worldwide
An investigation of the effect of small curvature resulted in the conclusion that the compressive strength of curved panels is equal to the strength of flat panels except for thick sheet where nonuniform curvature throughout the length of the panel may cause the strength of a curved panel to be as much as 10 to 15 percent less than the strength of a corresponding flat panel
3 editions published in 1933 in English and held by 7 WorldCat member libraries worldwide
An investigation of the effect of small curvature resulted in the conclusion that the compressive strength of curved panels is equal to the strength of flat panels except for thick sheet where nonuniform curvature throughout the length of the panel may cause the strength of a curved panel to be as much as 10 to 15 percent less than the strength of a corresponding flat panel
Effect of small deviations from flatness on effective width and buckling of plates in compression by Pai C Hu(
Book
)
2 editions published in 1946 in English and held by 7 WorldCat member libraries worldwide
(1) The effects of initial deviations from flatness upon buckle growth and effective width of plate are most marked at stresses around the theoretical flatplate critical stress; at stresses well above or below the critical stress, the behavior of a plate with an initial deviation from flatness is very much the same as that of an initially perfectly flat plate
2 editions published in 1946 in English and held by 7 WorldCat member libraries worldwide
(1) The effects of initial deviations from flatness upon buckle growth and effective width of plate are most marked at stresses around the theoretical flatplate critical stress; at stresses well above or below the critical stress, the behavior of a plate with an initial deviation from flatness is very much the same as that of an initially perfectly flat plate
The Pressure distribution over a modified elliptical wing tip on a biplane in flight by
Richard V Rhode(
Book
)
2 editions published in 1931 in English and held by 7 WorldCat member libraries worldwide
This note presents the results of flight pressure distribution tests on the right upper wing panel of a Douglas M3 airplane equipped with a modified elliptical tip having a slight amount of washout
2 editions published in 1931 in English and held by 7 WorldCat member libraries worldwide
This note presents the results of flight pressure distribution tests on the right upper wing panel of a Douglas M3 airplane equipped with a modified elliptical tip having a slight amount of washout
Local instability of symmetrical rectangular tubes under axial compression by
Eugene E Lundquist(
Book
)
3 editions published between 1938 and 1939 in English and held by 7 WorldCat member libraries worldwide
A chart is presented for the coefficient in the formula for the critical compressive stress at which crosssectional distortion begins in a thinwall tube of rectangular section symmetrical about its two principal axes. The energy method of Timoshenko was used in the theoretical calculations required for the construction of the chart. The deflection equation used in this method was selected to give good accuracy. The exact values given by solutino of the differential equation were calculated for a number of cases and it was found that the energy solution was correct to within a fraction of 1 percent
3 editions published between 1938 and 1939 in English and held by 7 WorldCat member libraries worldwide
A chart is presented for the coefficient in the formula for the critical compressive stress at which crosssectional distortion begins in a thinwall tube of rectangular section symmetrical about its two principal axes. The energy method of Timoshenko was used in the theoretical calculations required for the construction of the chart. The deflection equation used in this method was selected to give good accuracy. The exact values given by solutino of the differential equation were calculated for a number of cases and it was found that the energy solution was correct to within a fraction of 1 percent
Stability of structural members under axial load by
Eugene E Lundquist(
Book
)
3 editions published between 1937 and 1940 in English and held by 7 WorldCat member libraries worldwide
The principles of the Cross method of moment distribution are used to check the stability of structural members under axial load. A brief theoretical treatment of the subject, together with an illustrative problem, is included as a discussion of the reduced modulus at high stresses and a set of tables to aid in the solution of practical problems
3 editions published between 1937 and 1940 in English and held by 7 WorldCat member libraries worldwide
The principles of the Cross method of moment distribution are used to check the stability of structural members under axial load. A brief theoretical treatment of the subject, together with an illustrative problem, is included as a discussion of the reduced modulus at high stresses and a set of tables to aid in the solution of practical problems
A Method of estimating the critical buckling load for structural members by
Eugene E Lundquist(
Book
)
2 editions published between 1939 and 1940 in English and held by 7 WorldCat member libraries worldwide
The relations between load on the structure and rotation of a joint can be used to estimate the lowest critical load after the equation for neutral stability has been tested for three assumed critical loads, each of which is less than the lowest critical load
2 editions published between 1939 and 1940 in English and held by 7 WorldCat member libraries worldwide
The relations between load on the structure and rotation of a joint can be used to estimate the lowest critical load after the equation for neutral stability has been tested for three assumed critical loads, each of which is less than the lowest critical load
The Compressive strength of duralumin columns of equal angle section by
Eugene E Lundquist(
Book
)
2 editions published in 1932 in English and held by 7 WorldCat member libraries worldwide
Appendices are included giving excerpts from Army and Navy specifications for duralumin and approximate formulas for the properties of the equal angle section
2 editions published in 1932 in English and held by 7 WorldCat member libraries worldwide
Appendices are included giving excerpts from Army and Navy specifications for duralumin and approximate formulas for the properties of the equal angle section
A Study of general instability of box beams with trusstype ribs by
Eugene E Lundquist(
Book
)
2 editions published in 1942 in English and held by 6 WorldCat member libraries worldwide
The design of trusstype ribs for box beams is theoretically treated with regard to the function of the ribs in stabilizing the compression flange. The theory is applied to a design problem, and the results of this application are presented and discussed in relation to the general problem of rib design. The results of some tests made as a part of this general study are presented in an appendix
2 editions published in 1942 in English and held by 6 WorldCat member libraries worldwide
The design of trusstype ribs for box beams is theoretically treated with regard to the function of the ribs in stabilizing the compression flange. The theory is applied to a design problem, and the results of this application are presented and discussed in relation to the general problem of rib design. The results of some tests made as a part of this general study are presented in an appendix
Column and plate compressive strengths of aircraft structural materials. 24St aluminumalloy sheet by
Eugene E Lundquist(
Book
)
5 editions published in 1945 in English and held by 4 WorldCat member libraries worldwide
Column and plate compressive strengths of 24ST aluminumalloy sheet were determined both within and beyond the elastic range from tests of thinstrip columns and from localinstability tests of formed Z and channelsection 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, superseded preliminary results published previously
5 editions published in 1945 in English and held by 4 WorldCat member libraries worldwide
Column and plate compressive strengths of 24ST aluminumalloy sheet were determined both within and beyond the elastic range from tests of thinstrip columns and from localinstability tests of formed Z and channelsection 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, superseded preliminary results published previously
Extended tables of stiffness and carryover factor for structural members under axial load by
Eugene E Lundquist(
Book
)
3 editions published in 1944 in English and held by 3 WorldCat member libraries worldwide
The tables of stiffness and carryover factor that were presented in NACA Technical Note No. 652 have been extended to include the stiffness of a member with the far and subjected to a moment equal and opposite to the moment applied at the near end. These tables are of use in solving problems in the stability of structural members under axial load of moment distribution when the effects of axial load in the members are considered. The values presented are for structural members in which the cross section and the axial load do not vary along the length of the member. The interval between successive values of the argument is small enough to make interpolation unnecessary in engineering calculations
3 editions published in 1944 in English and held by 3 WorldCat member libraries worldwide
The tables of stiffness and carryover factor that were presented in NACA Technical Note No. 652 have been extended to include the stiffness of a member with the far and subjected to a moment equal and opposite to the moment applied at the near end. These tables are of use in solving problems in the stability of structural members under axial load of moment distribution when the effects of axial load in the members are considered. The values presented are for structural members in which the cross section and the axial load do not vary along the length of the member. The interval between successive values of the argument is small enough to make interpolation unnecessary in engineering calculations
The effect of initial displacement of the center support on the buckling of a column continous over three supports by
Eugene E Lundquist(
Book
)
3 editions published in 1940 in English and held by 3 WorldCat member libraries worldwide
A long column continuous over three supports was tested to determine its critical load when the center support was given amounts of initial displacement. During each test the middle support was hinged so as to be free to move parallel to the column axis during buckling
3 editions published in 1940 in English and held by 3 WorldCat member libraries worldwide
A long column continuous over three supports was tested to determine its critical load when the center support was given amounts of initial displacement. During each test the middle support was hinged so as to be free to move parallel to the column axis during buckling
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Aerodynamic load Aerodynamic loadMeasurement Aerodynamic loadTesting AerodynamicsResearch AeronauticsResearch AirplanesDesign and construction AirplanesMaterials AirplanesTesting AirplanesWings AirplanesWingsTesting Aluminum alloys Axial loads Bars (Engineering) Bending Box beamsTesting Buckling (Mechanics) Charts, diagrams, etc Columns CylindersPlastic properties Elastic analysis (Engineering) Elasticity Load factor design Loads (Mechanics) MaterialsCompression testing Mathematical analysis Monocoque construction Plates (Engineering) Shear (Mechanics) Sheetmetal Stability Stability of airplanes Strains and stresses Strength of materials Structural design Structural engineering Thinwalled structuresTesting Torsion TrussesTesting Tubes Turbulence Wind tunnel testing
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