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**Partner:**UNT Libraries Government Documents Department

**Year:**1943

**Serial/Series Title:**NACA Technical Notes

### Adaptor for measuring principal strains with Tuckerman strain gage

**Date:**June 1943

**Creator:**Mcpherson, A E

**Description:**An adapter is described which uses three Tuckerman optical strain gages to measure the displacement of the three vortices of an equilateral triangle along lines 120 degrees apart. These displacements are substituted in well-known equations in order to compute the magnitude and direction of the principal strains. Tests of the adaptor indicate that principal strains over a gage length of 1.42 inch may be measured with a systematic error not exceeding 4 percent and a mean observational error of the order of + or minus 0.000006. The maximum observed error in strain was of the order of 0.00006. The directions of principal strains for unidirectional stress were measured with the adaptor with an average error of the order of 1 degree.

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### 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

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### Bearing strengths of some wrought-aluminum alloys

**Date:**August 1, 1943

**Creator:**Moore, R L & Wescoat, C

**Description:**Although a number of investigations of the bearing strength of aluminum alloys have been made, the problem remains one of considerable interest to the aircraft industry. For this reason it has seemed advisable to make additional tests of the commonly used aircraft alloys in an effort to establish a better basis for the selection of allowable bearing values. Current design practice does not recognize the effect of edge distance upon bearing strengths, and for this reason edge distance was one of the principal variables considered in this investigation. The increasing emphasis being placed upon permanent set limitations makes it essential that more information on bearing yield phenomena be obtained. The object of this investigation was to determine bearing yield and ultimate strengths of the following aluminum alloy products: 17S-T, 24S-T, Alclad 24S-T, 24S-RT, 52S-0, 52S-1/2H, 52S-H, 53S-T, and 61S-T extrusions. Ratios of these bearing properties to tensile properties were also determined.

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### Bearing tests of magnesium-alloy sheet

**Date:**June 1, 1943

**Creator:**Sharp, W H & Moore, R L

**Description:**Bearing tests of AM-3S, AM-52S, and AM-C57S magnesium-alloy sheet in various thicknesses and tempers were made. Bearing yield and ultimate strengths were determined and compared for various edge distances and for various ratios of loading-pin diameter to sheet thickness. Tensile strengths were determined and ratios of average bearing yield and ultimate strength to tensile strength are given. The results of the tests indicated that ultimate bearing strengths increased with edge distances up to 1.5 to 2 times the diameter of the loading pin; that ultimate bearing strengths are a function of the ratio of pin diameter to sheet thickness; and that these properties are effected only slightly by increases in edge distance greater than 1.5 diameters.

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### Certain mechanical strength properties of aluminum alloys 25S-T and X76S-T

**Date:**October 1, 1943

**Creator:**Dolan, Thomas J

**Description:**None

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### Description of stress-strain curves by three parameters

**Date:**July 1, 1943

**Creator:**Ramberg, Walter & Osgood, William R

**Description:**A simple formula is suggested for describing the stress-strain curve in terms of three parameters; namely, Young's modulus and two secant yield strengths. Dimensionless charts are derived from this formula for determining the stress-strain curve, the tangent modulus, and the reduced modulus of a material for which these three parameters are given. Comparison with the tensile and compressive data on aluminum-alloy, stainless-steel, and carbon-steel sheet in NACA Technical Note No. 840 indicates that the formula is adequate for most of these materials. The formula does not describe the behavior of alclad sheet, which shows a marked change in slope at low stress. It seems probable that more than three parameters will be necessary to represent such stress-strain curves adequately.

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### Effect of fillers and of mixing procedure on the strength of plastic materials

**Date:**January 1, 1943

**Creator:**Kynoch, William & Patronsky, L A

**Description:**None

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### The effect of inlet-valve design, size, and lift on the air capacity and output of a four-stroke engine

**Date:**November 1, 1943

**Creator:**Livengood, James C & Stanitz, John D

**Description:**None

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### Effect of rivet pitch upon the fatigue strength of single-row riveted joints of 0.025- to 0.025-inch 24S-T alclad

**Date:**July 1, 1943

**Creator:**Seliger, Victor

**Description:**S-N curves at the range ratio of 0.2 were experimentally obtained for each of the following values of rivet pitch P as used in a single-row lap joint of 0.025- to 0.025-inch 24S-T alclad with one-eight AN430 round-head rivets: p=0.5, 0.75, 1.0, 1.5. Families of constant rivet pitch curves, which define the fatigue life for specimens studied, were developed. Curves showing the variation of the effective stress concentration factor in fatigue with rivet pitch and maximum load per rivet were also established.

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### 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

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### The effect of the type of specimen on the shear strengths of driven rivets

**Date:**November 1, 1943

**Creator:**Sharp, W H

**Description:**None

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### Effects of prior fatigue-stressing of the impact resistance of chromium-molybdenum aircraft steel

**Date:**March 1, 1943

**Creator:**Kies, J A & Holshouser, W L

**Description:**None

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### The exact solution of shear-lag problems in flat panels and box beams assumed rigid in the transverse direction

**Date:**January 1, 1943

**Creator:**Hildebrand, Francis B

**Description:**A mathematical procedure is herein developed for obtaining exact solutions of shear-lag problems in flat panels and box beams: the method is based on the assumption that the amount of stretching of the sheets in the direction perpendicular to the direction of essential normal stresses is negligible. Explicit solutions, including the treatment of cut-outs, are given for several cases and numerical results are presented in graphic and tabular form. The general theory is presented in a from which further solutions can be readily obtained. The extension of the theory to cover certain cases of non-uniform cross section is indicated. Although the solutions are obtained in terms of infinite series, the present developments differ from those previously given in that, in practical cases, the series usually converge so rapidly that sufficient accuracy is afforded by a small number of terms. Comparisons are made in several cases between the present results and the corresponding solutions obtained by approximate procedures devised by Reissner and by Kuhn and Chiarito.

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### A hot-wire circuit with very small time lag

**Date:**February 1, 1943

**Creator:**Weske, John R

**Description:**A circuit for a hot-wire anemometer for the measurement of fluctuating flow is presented in the present report. The principal elements of the circuit are a Wheatstone bridge, one branch of which is the hot wire; and an electronic amplifier and a current regulator for the brief current which in combination maintain the bridge balance constant. Hence the hot wire is kept at practically constant resistance and temperature, and the time lag caused by thermal inertia of the wire is thereby reduced. Through the addition of a nonlinear amplifying stage the reading of the instrument has been rendered proportional to the velocity. A discussion of certain characteristics of the circuit and the results of related calibrating tests are given.

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### Large-deflection theory for end compression of long rectangular plates rigidly clamped along two edges

**Date:**January 1, 1943

**Creator:**Levy, Samuel & Krupen, Philip

**Description:**The von Karman equations for flat plates are solved beyond the buckling load up to edge strains equal to eight time the buckling strain, for the extreme case of rigid clamping along the edges parallel to the load. Deflections, bending stresses, and membrane stresses are given as a function of end compressive load. The theoretical values of effective width are compared with the values derived for simple support along the edges parallel to the load. The increases in effective width due to rigid clamping drops from about 20 percent near the buckling strain to about 8 percent at an edge strain equal to eight times the buckling strain. Experimental values of effective width in the elastic range reported in NACA Technical Note No. 684 are between the theoretical curves for the extremes of simple support and rigid clamping.

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### Large-deflection theory of curved sheet

**Date:**May 1, 1943

**Creator:**Levy, Samuel

**Description:**Equations are given for the elastic behavior of initially curved sheets in which the deflections are not small in comparison with the thickness, but at the same time small enough to justify the use of simplified formulas for curvature. These equations are solved for the case of a sheet with circular cylindrical shape simply supported along two edges parallel to the axis of the generating cylinder. Numerical results are given for three values of the curvature and for three ratios of buckle length to buckle width. The computations are carried to buckle deflections of about twice the sheet thickness. It was concluded that initial curvature may cause an appreciable increase in the buckling load but that, for edge strains which are several times the buckling strain, the initial curvature causes a negligibly small change in the effective width.

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### Least-work analysis of the problem of shear lag in box beams

**Date:**January 1, 1943

**Creator:**Hildebrand, Francis B & Reissner, Eric

**Description:**The distribution of stress in the cover sheets of thin-wall box beams is analyzed, with regard to the effect of shear deformation in the cover sheets, by the method of least work. Explicit results are obtained for a number of representative cases that show the influence of the following factors on the stress patterns. (1) Variation of stress in spanwise direction as given by elementary beam theory. (2) Value of a parameter called shear-lag aspect ratio which designates the product of span-width ratio of the beam and of the square root of the ratio of effective shear modulus and tensing modulus of the cover sheets. (3) Value of ratio of cover-sheet stiffness to side-web stiffness. (4) Variation of beam height in span direction. (5) Variation of beam width in span direction. (6) Variation of cover-sheet thickness in span direction. General conclusions are drawn from the results obtained. Among them the most important one appears to be the fact that the shear-lag effect depends primarily on the following tow quantities: (1) the value of the shear-lag aspect ratio. (2) the shape of the curve representing the product of the stress of elementary beam theory and of the cover-sheet thickness.

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### A method for determining the column curve from tests of columns with equal restraints against rotation on the ends

**Date:**August 1, 1943

**Creator:**Lundquist, Eugene E; Rossman, Carl A & Houbolt, John C

**Description:**The results are presented of a theoretical study for the determination of the column curve from tests of column specimens having ends equally restrained against rotation. The theory of this problem is studied and a curve is shown relating the fixity coefficient c to the critical load, the length of the column, and the magnitude of the elastic restraint. A method of using this curve for the determination of the column curve for columns with pin ends from tests of columns with elastically restrained ends is presented. The results of the method as applied to a series of tests on thin-strip columns of stainless steel are also given.

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### Methods of Measurement of High Air Velocities by the Hot-Wire Method

**Date:**February 1, 1943

**Creator:**Weske, John R.

**Description:**Investigations of strengths of hot wires at high velocities were conducted with platinum, nickel, and tungsten at approximately 200 Degrees Celcius hot-wire temperature. The results appear to disqualify platinum for velocities approaching the sonic range; whereas nickel withstands sound velocity, and tungsten may be used for supersonic velocities under standard atmospheric conditions. Hot wires must be supported by rigid prolongs at high velocities to avoid wire breakage. Resting current measurements for constant temperature show agreement with King's relation.

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### Part-throttle operation and control of a piston-ported two-stroke cylinder

**Date:**November 1, 1943

**Creator:**Rogowski, A R & Taylor, C Fayette

**Description:**None

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### A portable calibrator for dynamic strain gages

**Date:**February 1, 1943

**Creator:**Mcpherson, Albert E

**Description:**A portable device for calibrating dynamic strain gages is described. The device contains a motor-driven cam, which applies alternating tensile loads to a metal strip 5/8 inch wide and 6 1/4 inches long. The cam is designed to produce a nearly sinusoidal variation of strain with time. Dynamic strain gages with gage lengths up to 5 inches may be calibrated by mounting them on the strip and by changing the frequency and the amplitude of the tensile load. The frequency may be varied from 15 to 30 cycles per second and the strain amplitude from 0 to 10x10-4 in steps of 2x10-4.

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### Pressure Distribution on the Fuselage of a Midwing Airplane Model at High Speeds

**Date:**February 1, 1943

**Creator:**Delano, James B

**Description:**None

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### Requirements for auxiliary stiffeners attached to panels under combined compression and shear

**Date:**September 16, 1943

**Creator:**Scott, Merit & Weber, Robert L

**Description:**Panels of aluminum alloy sheets, framed by side and end stiffeners, were subjected to combined loading by means of offset knife edges applying loads to top and bottom end plates with reacting forces against the end plates supplied by laterally acting rollers. The test specimens were 17S-T aluminum alloy shoots 0.040 inch thick in panels of 10-inch width and three different lengths (approximately 10, 26, and 30 inch). Data were obtained for the bowing of transverse and longitudinal ribs of rectangular cross section and varying depths mounted on one side of the sheet only, for several ratios of compression to shear loads. Limiting values of the moments of inertia were calculated from these measurements. The experimental values exceed the theoretical values given by Timoshenko for the case of simply supported sheets with uniformly distributed boundary stresses. The work reported includes measurements of the effective shear moduli of the nine test panels with and without ribs. These data are compared with values published by Lahdo and Wagner.

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### Round heat-treated chromium-molybdenum-steel tubing under combined loads

**Date:**July 1, 1943

**Creator:**Osgood, William R

**Description:**The results of tests of round heat-treated chromium-molybdenum-steel tubing are presented. Tests were made on tubing under axial load, bending load, torsional load, combined bending and axial load, combined bending and torsional load, and combined axial, bending, and torsional load. Tensile and compressive tests were made to determine the properties of the material. Formulas are given for the evaluation of the maximum strength of this steel tubing under individual or combined loads. The solution of an example is included to show the procedure to be followed in designing a tubular cantilever member to carry combined loads.

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