Describes the varieties of standard containers for shipping fresh fruits and vegetables, and their costs and uses. Recommends simplification to reduce the burdens caused by the lack of uniformity in containers.

From Summary: "An experimental investigation was conducted to determine the penetration of air jets directed perpendicularly to an air stream. Jets issuing from circular, square, and elliptical orifices were investigated and the jet penetration at a position downstream of the orifice was determined- as a function of jet density, jet velocity, air-stream density, air-stream velocity, effective jet diameter, and orifice flow coeffIcient. The jet penetrations were determined for nearly constant values of air-stream density at three tunnel-air velocities arid for a large range of jet velocities and densities."

Report presenting tables for determining the total-absorption coefficients as well was the intensities and spectral distribution of gamma rays at any scattering angle. Both experimental and computed data on gamma rays of quantum energies up to 20 million electron volts for all elements which have significant data available are provided. The accuracy of results is obtained by the use of tables.

Report presenting an investigation to determine the feasibility of bearing lubrication by a process involving the transfer of molybdenum disulfide from within the structure of a composite bearing material to the interface between the contacting surfaces. The experiments were performed with a kinetic-friction apparatus employing a rotating steel disk and a bearing-specimen assembly suspended and restrained by metal springs.

"The slip theory of plasticity is applied to the problem of calculating the strains associated with biaxial tension for the case of constant stress ratios and is found to be in better agreement with experiment than the octahedral-shear and maximum-shear theories usually employed to analyze such data" (p. 1).

Note presenting surface-tension measurements from room temperature to 180 degrees Celsius of a series of aeronautical lubricating oils and a few liquids of associated interest. The critical temperatures of the liquids are calculated and a general classification of existing oils into three groups is provided.

Note presenting comparative data on the volume of foam and stability of foams of aeronautical lubricating oils produced at 100 degrees Celsius by the air-bubbling method. All of the data were obtained with the same foam meter, by a standard technique, and at various rates of air flow. Results regarding the reproducibility of foam tests and treatment of data are provided.

Note presenting an investigation of nine hydrocarbons mixed in pairs, sealed in glass tubes, and foamed by shaking in order to examine the foaming properties of the hydrocarbons. Results for benzene, toluene, xylene, cumene, butyl benzene, isopentane, octene, octane, and decane are provided.

Note presenting measurements of the rates of rise of small air bubbles, up to 2 millimeters in diameter, at room temperature in an undoped oil, in the same oil containing foam inhibitors, and in an oil containing lubricating additives. The apparent diameter of the air bubbles was measured visually through an ocular micrometer on a traveling telescope. A method is derived to calculate the thickness of the liquid shell which would have to move with the bubbles in the doped oils to account for the abnormally slow velocity.

Report presenting an approximate method for determining the pressure distribution due to unsteady motion for thin wings of fairly general plan form. The method is valid for arbitrary motions when the second derivative of the perturbation velocities with respect to time is not large.

Report presenting the equations of motion of a conventional airplane penetrating a gust in order to determine the effects due to stability on the gust load factor. A numerical method is derived in matrix notation which affords a systematic procedure of solving the equations for a unit jump or arbitrary forcing function. Sample calculations were performed to illustrate the application of the equations.

Note presenting an investigation using microscopic observation of the action to determine the cause of fretting corrosion. Glass and other noncorrosive materials, as well as metals, were used as specimens. Results regarding metal against metal, metal against nonmetal, and nonmetals against nonmetals are provided.

Report presenting an investigation to determine the influence of aspect ratio, boundary-layer control by means of slots and porous surfaces, Reynolds number, and tunnel end-wall condition on the performance of airfoils in cascade. A representative compressor-blade section of three aspect ratios has been tested at low speeds in cascades with solid and porous side walls.

From Summary: "A small-deflection theory that takes into account deformations due to transverse shear is presented for the elastic-behavior analysis of orthotropic plates of constant cylindrical curvature, with considerations of buckling included. The theory is applicable primarily to sandwich construction."

Note presenting shear fatigue tests of joints with rivets in Alclad sheet of several high-strength aluminum alloys. The results showed that the design of the joint gives a wider range of fatigue strengths than does the choice of material from the group studied. No one sheet alloy showed superiority over the others.

Report presenting the results of an investigation in the full-scale tunnel of the static longitudinal stability and control of a convertible-type airplane as affected by articulated- and rigid-propeller operation. The investigation included force measurements for a large angle-of-attack range of the model with the all-movable horizontal tail installed and removed. Results regarding the static longitudinal stability and control at normal-flight altitudes and transition range are provided.

Results presenting testing of a model with heavy beam loading and an angle of dead rise of 30 degrees subjected to smooth-water impacts in the Langley impact basin. Testing was made at fixed trims of 6 degrees, 15 degrees, 30 degrees, and 45 degrees for a range of flight-path angles and consistent beam-loading coefficient. Time histories of horizontal and vertical displacements, vertical velocity, vertical acceleration, and pitching moment are provided.

Note presenting an investigation of a thin, faired, double-wedge airfoil section with plain nose flaps with chords equal to 12, 16, 20, and 25 percent of the airfoil chord. Section lift, drag, and pitching-moment data were obtained at a Reynolds number of 5.8 million and a Mach number of 0.17. A greater positive shift in the angle of attack for zero lift and more negative pitching moments resulted from increasing chord of the nose flap.

Note presenting a method for determining the rate of roll of free-flight aerodynamic models by means of polarized radio waves. The discussion shows that through the use of the technique, the direction of roll, as well as zero roll, is uniquely determined. Analysis of the data obtained and data accuracy are discussed and examples are given to show how the record-reduction method affects the accuracy of the data.

Note presenting an investigation conducted on an aircraft liquid-cooled single-cylinder test engine equipped with direct fuel injection to determine the effect of valve overlap and compression ratio on variation of engine power and specific fuel consumption with exhaust pressure. Results regarding the experimental engine data and compound-power-plant performance are provided.

"The equation of vertical motion for an airplane in gusty air is simplified in order that its solution is a function of only two parameters, namely, the mass parameter of the airplane and the shape of the gust the airplane is penetrating. The solutions of the equation are presented in the form of charts that can be used for estimating rapidly and easily the acceleration ratios encountered by airplanes with different mass parameters penetrating a sharp-edge gust, a gust of arbitrary shape, or a triangular gust.

Report presenting an investigation to determine the relative resistance of six cast high-temperature alloys to cracking caused by thermal shock. The alloys tested included S-816, S-590, Vitallium, 422-19, X-40, and Stellite 6. Results regarding the tabulation of cycles to failure, crack properties, metallographic examination, and some curves of deformation data are provided.

"Results are presented of compressive stress-strain tests of titanium sheet at temperatures from room temperature up to 800 degrees Fahrenheit, exposure times of 1/2 to 2 hours, and strain rates of 0.002 to 0.006 per minute. The results show that titanium has favorable compressive properties, comparable to those in tension, up through 800 degrees Fahrenheit. Marked anisotropy in compression was also noted" (p. 1).

Report presenting an investigation of using two suction slots in order to determine the effectiveness of a nose slot at higher values of lift. The suction through the midchord slot in conjunction with the nose slot resulted in substantial gains in the maximum lift over that obtainable with nose suction alone. Results regarding the lift, drag, and moment characteristics, pressure distribution, boundary-layer measurements, and plenum-chamber pressures are provided.