From Introduction: "The purpose of the present paper is twofold. First, a close connection will be established between reverse-flow theorems in subsonic and supersonic, steady-state wing theory and known reciprocity relations between two solutions of the equation the flow field."

Note presenting an experimental program to study the subject of metal fatigue and to determine and evaluate the fundamental factors which influence the behavior. The statistics of the fatigue-fracture curves and endurance limits were determined for a variety of metals and the effects of some metallurgical factors on the statistical nature of fatigue properties were shown.

Note presenting a general theory of steady three-dimensional flow of a nonviscous fluid in subsonic and supersonic turbomachines with arbitrary hub and casing shapes and a finite number of blades. The equations obtained to describe the fluid flow on these stream surfaces show clearly the several approximations involved in ordinary two-dimensional treatments.

Report presenting the use of linearized theory for compressible unsteady flow to obtain the velocity potential and lift and moment for a thin, harmonically oscillating, two-dimensional wing-aileron combination moving at sonic speed.

Report presenting an analysis of airfoil data from several NACA 16-series propeller airfoils from tests of 5-inch chord models in the 24-inch high-speed tunnel and 12-inch-chord models in the 8-foot high-speed tunnel. Results indicated that differences of less than 1 percent in propeller efficiency at or near the design condition will be involved in applying data from 5-inch-chord and 12-inch-chord airfoil tests to full-scale propeller design.

Report presenting experimental data obtained in the 4- by 4-foot supersonic tunnel for a parabolic body of revolution of large fineness ratio at mach number 1.59, which are analyzed in order to locate positions at which static-pressure orifices will indicate a constant static pressure independent of the pitch-yaw attitude of the body.

Report presenting a general method of design is developed for two-dimensional unbranched channels with prescribed velocities as a function of arc length along the channel walls. The method is developed for both incompressible and compressible, irrational, nonviscous flow. Five numerical examples are given including three elbow designs with the same prescribed velocity as a function of arc length along the channel walls but with incompressible, linearized compressible, and compressible flow.

"An impulse-momentum method for determining impact conditions for landing gears in eccentric landings is presented. The analysis is primarily concerned with the determination of contact velocities for impacts subsequent to initial touchdown in eccentric landings and with the determination of the effective mass acting on each landing gear. These parameters determine the energy-absorption requirements for the landing gear and, in conjunction with the particular characteristics of the landing gear, govern the magnitude of the ground loads" (p. 1).

Note presenting the use of the Crocco method to solve the simultaneous differential equations of momentum and energy involved in the flow of air in a thin laminar boundary layer on a flat plate. The Crocco method was used because it gave accurate results for arbitrary Prandtl number near unity. Variations of shear, velocity, temperature, and Mach number across the boundary layer are included.

"A coincidence Geiger counter system was constructed for the absolute measurement of the activity of radioactive substances made in a cyclotron. The average beam current in the cyclotron can be calculated from the number of disintegrations per second observed, the half-life of the radioactive substance, and the reaction cross section" (p. 1).

Report presenting the indical lift and moment functions for sinking and pitching motion at Mach numbers 0.5 and 0.6. The functions are determined from a knowledge of existing oscillatory coefficients at low reduced frequencies and from approximate expressions of the coefficients at high reduced frequencies. Results regarding determination of indical functions, considerations for indical lift due to penetration of a sharp-edge gust, and approximation of indical functions by analytic expressions are provided.

Report presenting an investigation of the results at high Reynolds numbers and low Mach numbers to determine the maximum-lift and stalling characteristics of an aspect-ratio-4 trapezoidal wing with 10-percent-thick, circular-arc airfoil sections. Testing occurred measurements of lift, drag, and pitching-moment coefficients of the basic wing and of the wing with 0.20-chord droop-nose and rear flaps deflected alone and in combination with one another.

Report presenting an exploratory investigation of the dynamic effects of fuel sloshing in tip tanks on suddenly excited bending oscillations using two simplified model beam-tank systems. Several fluids of different densities and viscosities were used in combination with various conditions of tank fullness. Results regarding the large and small beam-tank system are provided.

Report presenting an investigation in order to study the characteristics of flow in the vicinity of a rectangular wing of aspect ratio 0.25 with a modified flat-plate airfoil section. The investigation was conducted using photographs of a tuft grid located at a number of chordwise positions along the airfoil and behind the trailing edge. Results regarding the force-tests, formation of vortices and vorticity distribution in the wake, location of vortex cores, and chordwise growth of lift are provided.

Report presenting the use of molybdenum disulfide as a solid film lubricant in applications where designs or temperatures preclude liquid lubricants is dependent on successful bonding of the powder to the surface to be lubricated. An investigation was conducted to determine the basic mechanism of bonding and to extend application of the bonding to a variety of materials. Results regarding an examination of electron diffraction of MoS2 dusted and rubbed on steel, adherence of dry powders to metals, chemical action in bonding mechanism, other resin-forming liquid vehicles, bonding of MoS2 and other powders to various materials, and analysis of solid film by electron diffraction are provided.

Report presenting average and local skin-friction coefficients for laminar flow on a plate plate at Mach number 2.4 and compared with the laminar-boundary-layer theory of Chapman and Rubesin. The average skin-friction coefficients were calculated by the momentum-loss method from impact-pressure surveys of the boundary layer.

Report presenting an investigation in the low-turbulence pressure tunnel to determine the effects of Mach and Reynolds number on the maximum lift characteristics of the NACA 65-006, 64-009, 64-210, and 64(sub 2)-215 airfoil sections in smooth and leading-edge roughness conditions. A range of Mach and Reynolds numbers were explored.

Report presenting burst testing conducted on several designs of sound disks and disks with defects. Results were compared with tensile strength, tensile ductility, and notch tensile strength. The main purpose of the investigation was to determine the extent to which disk strength can be increased by increasing tensile strength, to investigate the extent to which a correlation exists between disk strength and mechanical properties, and to present data on the influence of several types of stress concentration on the strength of disks made from ductile and brittle materials.

Note presenting tests to determine local heat-transfer coefficients and friction factors for fully developed turbulent flow of air in a smooth electrically heated tube with an inside diameter of 0.87 inch and a length of 87 inches. Testing occurred at high ratios of wall to fluid bulk temperatures. Results regarding the predicted temperature and velocity distributions, Nusslet numbers, friction factors, velocity distributions, and temperature distributions are provided.

From Summary: "Theoretical solutions are presented for the buckling in uniform axial compression of two types of simply supported curved sandwich plates: the corrugated-core type and the isotropic-core type. The solutions are obtained from a theory for orthotropic curved plates in which deflections due to shear are taken into account. Results are given in the form of equations and curves."

Note presenting a survey of the chromium-cobalt-nickel ternary phase diagram at 1200 degrees Celsius by means of microscopic and X-ray diffraction studies on 110 vacuum-melted alloys prepared from commercial metals of the highest purity available. Three distinct phases are noted.

Note presenting a discussion of a semiempirical profile correction factor which enables the estimation of the wave drag due to thickness at supersonic speeds for three-dimensional wings with arbitrary airfoil section through use of previously calculated drag coefficients. Application of the correction factor to the known drag coefficients of some rhombic-profile wings yielded estimates for the drag coefficients of parabolic-arc-profile wings that were in good agreement with theoretically calculated values.

Report presenting a method permitting the calculation of local heat transfer around the periphery of cylinders of arbitrary cross section in the laminar region for flow of a fluid with constant property values with an accuracy sufficient for engineering purposes. The method is applied to circular and elliptic cylinders are the results are described.

"An isothermal survey was made of certain portions of the chromium-cobalt-nickel-iron quaternary system at 1200 degrees Celsius. The iron content was varied up to 30 percent to include the range of commercial chromium-cobalt-nickel alloys. As a part of the quaternary system, the cobalt-chromium-iron ternary system was also studied" (p. 1).