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 Decade: 1940-1949
 Year: 1946
 Collection: National Advisory Committee for Aeronautics Collection
The Lagrangian Multiplier Method of Finding Upper and Lower Limits to Critical Stresses of Clamped Plates

The Lagrangian Multiplier Method of Finding Upper and Lower Limits to Critical Stresses of Clamped Plates

Date: January 1, 1946
Creator: Hu, Pai C. & Budiansky, Bernard
Description: The theory of Lagrangian multipliers is applied to the problem of finding both upper and lower limits to the true compressive buckling stress of a clamped rectangular plate. The upper and lower limits thus bracket the truss, which cannot be exactly found by the differential-equation approach. The procedure for obtaining the upper limit, which is believed to be new, presents certain advantages over the classical Raleigh-Rite method of finding upper limits. The theory of the lower-limit procedure has been given by Trefftz but, in the present application, the method differs from that of Trefftz in a way that makes it inherently more quickly convergent. It is expected that in other buckling problems and in some vibration problems problems the Lagrangian multiplier method finding upper and lower limits may be advantageously applied to the calculation of buckling stresses and natural frequencies.
Contributing Partner: UNT Libraries Government Documents Department
Single-cylinder oil-control tests of porous chrome plated cylinder barrels for radial air-cooled engines

Single-cylinder oil-control tests of porous chrome plated cylinder barrels for radial air-cooled engines

Date: January 1, 1946
Creator: Swikert, Max
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts of thermodynamic properties of fluids encountered in calculations of internal combustion engine cycles

Charts of thermodynamic properties of fluids encountered in calculations of internal combustion engine cycles

Date: May 1, 1946
Creator: Hottel, H C & Williams, G C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A fixture for compressive tests of thin sheet metal between lubricated steel guides

A fixture for compressive tests of thin sheet metal between lubricated steel guides

Date: April 1, 1946
Creator: Miller, James A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of sweepback and aspect ratio on longitudinal stability characteristics of wings at low speeds

Effect of sweepback and aspect ratio on longitudinal stability characteristics of wings at low speeds

Date: July 1, 1946
Creator: Shortal, Joseph A & Maggin, Bernard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The theoretical flow of a frictionless, adiabatic, perfect gas inside of a two-dimensional hyperbolic nozzle

The theoretical flow of a frictionless, adiabatic, perfect gas inside of a two-dimensional hyperbolic nozzle

Date: May 1, 1946
Creator: Emmons, Howard W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A study of combustion in a flowing gas

A study of combustion in a flowing gas

Date: April 1, 1946
Creator: Gilbert, Mitchell; Haddock, Gordon & Metzler, Allen
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Numerical procedures for the calculation of the stresses in monocoques III : calculation of the bending moments in fuselage frames

Numerical procedures for the calculation of the stresses in monocoques III : calculation of the bending moments in fuselage frames

Date: January 1, 1946
Creator: Hoff, N J; Libby, Paul A & Klein, Bertran
Description: This report deals with the calculation of the bending moments in and the distortions of fuselage rings upon which known concentrated and distributed loads are acting. In the procedure suggested, the ring is divided into a number of beams each having a constant radius of curvature. The forces and moments caused in the end sections of the beams by individual unit displacements of the end sections are listed in a table designated as the operations table in conformity with Southwell's nomenclature. The operations table and the external loads are equivalent to a set of linear equations. For their solution the following three procedures are presented: 1) Southwell's method of systematic relaxations. This is a step-by-step approximation procedure guided by the physical interpretation of the changes in the values of the unknown. 2) The growing unit procedure in which the individual beams are combined successively into beams of increasing length until finally the entire ring becomes a single beam. In each step of the procedure a set of not more than three simultaneous linear equations is solved. 3) Solution of the entire set of simultaneous equations by the methods of the matrix calculus. In order to demonstrate the manner in which ...
Contributing Partner: UNT Libraries Government Documents Department
Flow over a slender body of revolution at supersonic velocities

Flow over a slender body of revolution at supersonic velocities

Date: July 8, 1946
Creator: Jones, Robert T & Margolis, Kenneth
Description: The theory of small disturbances is applied to the calculation of the pressure distribution and drag of a closed body of revolution traveling at supersonic speeds. It is shown that toward the rear of the body the shape of the pressure distribution is similar to that for subsonic flow. For fineness ratios between 10 and 15 the theoretical wave drag is of the same order as probable values of the frictional drag.
Contributing Partner: UNT Libraries Government Documents Department
Stresses in and general instability of monocoque cylinders with cutouts I : experimental investigation of cylinders with a symmetric cutout subjected to pure bending

Stresses in and general instability of monocoque cylinders with cutouts I : experimental investigation of cylinders with a symmetric cutout subjected to pure bending

Date: January 1, 1946
Creator: Hoff, N J & Boley, Bruno A
Description: Ten 24S-T alclad cylinders of 20-inch diameter, 45- or 58-inch length, and 0.012-inch wall thickness, reinforced with 24S-T aluminum alloy stringers and rings were tested in pure bending. In the middle of the compression side of the cylinders there was a cutout extending over 19 inches in the longitudinal direction, and over an angle of 45 degrees, 90 degrees, or 135 degrees in the circumferential direction. The strain in the stringers and in the sheet covering was measured with metal electric strain gages. The stress distribution in the cylinders deviate considerably from the linear law valid for cylinders without a cutout. The maximum strain measured was about four-thirds of the value calculated from the Mc/I formula when I was taken as the moment of inertia of the cross section of the portion of the cylinder where the cutout was situated. A diagram is presented containing the strain factors defined as the ratios of measured strain to strain calculated with the Mc/I formula. All the 10 cylinders tested failed in general instability. Two symmetric and one antisymmetric pattern of buckling were observed and the buckling load appeared to be independent of the method of manufacture and the length of the cylinder. ...
Contributing Partner: UNT Libraries Government Documents Department
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