Lundquist, Eugene E.
Overview
Works:  48 works in 97 publications in 1 language and 267 library holdings 

Roles:  Author, Contributor 
Classifications:  TL501, 
Publication Timeline
.
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 11 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 11 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 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
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 8 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 8 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 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 8 WorldCat member libraries worldwide
This note presents the results obtained in pressure distribution tests on the right upper wing panel and tip of a Douglas M3 airplane in flight. These tests are a part of a more extensive investigation of the effect of changes in tip shape on the load distribution, the tip reported herein being the first of a series of six shapes being tested
2 editions published between 1930 and 1931 in English and held by 8 WorldCat member libraries worldwide
This note presents the results obtained in pressure distribution tests on the right upper wing panel and tip of a Douglas M3 airplane in flight. These tests are a part of a more extensive investigation of the effect of changes in tip shape on the load distribution, the tip reported herein being the first of a series of six shapes being tested
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
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 8 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 8 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
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
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 7 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 7 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
This report gives a comparison of the accuracy of three methods for calculating the compressive strength of flat sheet and stiffener combinations such as occur in stressedskin or monocoque structures for aircraft. Of the three methods based upon various assumptions with regard to the interaction of sheet and stiffener, the method based upon mutual action of the stiffenerand an effective width of sheet as a column gave the best agreement with the results of tests
3 editions published in 1933 in English and held by 7 WorldCat member libraries worldwide
This report gives a comparison of the accuracy of three methods for calculating the compressive strength of flat sheet and stiffener combinations such as occur in stressedskin or monocoque structures for aircraft. Of the three methods based upon various assumptions with regard to the interaction of sheet and stiffener, the method based upon mutual action of the stiffenerand an effective width of sheet as a column gave the best agreement with the results of tests
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
This report presents a chart giving the compressive strength of duralumin columns of equal angle section. The data used in the construction of the chart were obtained from various published sources and were correlated with theory in the range where secondary failure occurred
2 editions published in 1932 in English and held by 7 WorldCat member libraries worldwide
This report presents a chart giving the compressive strength of duralumin columns of equal angle section. The data used in the construction of the chart were obtained from various published sources and were correlated with theory in the range where secondary failure occurred
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 7 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 7 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
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 solutions of six simple problems are included to illustrate the application of the method of estimating critical loads and to reveal certain characteristics of the method that should be known by the practical engineer using it. Four of these problems are concerned with members that lie in the elastic, or longcolumn, range. The other two problems are concerned with memberes that lie in the shortcolumn range
2 editions published between 1939 and 1940 in English and held by 7 WorldCat member libraries worldwide
The solutions of six simple problems are included to illustrate the application of the method of estimating critical loads and to reveal certain characteristics of the method that should be known by the practical engineer using it. Four of these problems are concerned with members that lie in the elastic, or longcolumn, range. The other two problems are concerned with memberes that lie in the shortcolumn range
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
Critical compressive stress for outstanding flanges by
Eugene E Lundquist(
Book
)
2 editions published in 1942 in English and held by 6 WorldCat member libraries worldwide
2 editions published in 1942 in English and held by 6 WorldCat member libraries worldwide
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 6 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 6 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 columns with I, Z channel, and rectangular tube sections by
Elbridge Z Stowell(
Book
)
2 editions published between 1939 and 1940 in English and held by 6 WorldCat member libraries worldwide
The calculation of the critical compressive stress at stresses above the elastic range is briefly discussed. In order to demonstrate the use of the formulas and the charts in engineering calculations, two illustrative problems are included
2 editions published between 1939 and 1940 in English and held by 6 WorldCat member libraries worldwide
The calculation of the critical compressive stress at stresses above the elastic range is briefly discussed. In order to demonstrate the use of the formulas and the charts in engineering calculations, two illustrative problems are included
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 continuous over three supports by
Eugene E Lundquist(
Book
)
2 editions published in 1940 in English and held by 1 WorldCat member library worldwide
A long column continuous over three supports was tested to determine its critical load when the center support was given varying 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
2 editions published in 1940 in English and held by 1 WorldCat member library worldwide
A long column continuous over three supports was tested to determine its critical load when the center support was given varying 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
Aeronautics. Seventeenth annual report of the National Advisory Committee for Aeronautics. 1931. Including Technical Reports
Nos. 365 to 400(
)
1 edition published in 1932 in English and held by 0 WorldCat member libraries worldwide
1 edition published in 1932 in English and held by 0 WorldCat member libraries worldwide
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Aerodynamic load Aerodynamic loadMeasurement Aerodynamic loadTesting AerodynamicsResearch AeronauticsResearch AirplanesDesign and construction AirplanesMaterials AirplanesTesting AirplanesWings AirplanesWingsTesting Aluminum alloys Axial loads Bending Buckling (Mechanics) Charts, diagrams, etc Columns CylindersPlastic properties Elastic analysis (Engineering) Elasticity Load factor design Loads (Mechanics) MaterialsCompression testing MaterialsFatigue 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 Tubes Turbulence Wind tunnel testing
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