Report presenting a paper in two parts about transition and turbulent boundary layers. The first part reviews the current problem of the instability of laminar boundary layers. The second part reviews the current state of knowledge of the mechanics of turbulent boundary layers and of the methods now being used for fundamental studies of the turbulent fluctuations in turbulent boundary layers.

Report from the U.S. Bureau of Mines on studies conducted on the reservoir oils of Elk Hills field. Methods and instrumentation used in the studies are presented. This report includes tables, graphs, and maps.

Report issued by the Bureau of Mines on studies of coal deposits of the Coal Creek district. The physicality, geology, and characteristics of samples are listed. This report includes tables, and a map.

Note presenting photographic records of the behavior of a blade in flight as obtained with a conventional single-rotor helicopter. The results of the measurements of flapping motion, in-plane motion, and blade distortions are presented for selected conditions of flight at tip-speed ratios ranging from 0.12 to 0.25. Plots of blade twisting and blade bending in the plane of flapping are presented for a sample case.

Note presenting the results of glide performance tests conducted on a test helicopter with its original production blades in the autorotation condition. The data was reduced to coefficient form, and performance at standard sea-level conditions were calculated.

Note presenting an investigation of the laminar boundary layer and the position of the transition point on a heated flat plate. The Reynolds number of transition was found to decrease as the temperature of the plate is increased. Results regarding the effect of surface temperature, effect of roughness elements, mean-velocity profile near a heated wall, instability of inflection-point profiles, and laminar separation and transition are provided.

From Introduction: "An investigation was made to determine the relative significance of the factors that affect the exhaust process; the effects that an exhaust-process change has on cylinder charging were given special attention. Differential equations of this nature have been developed by Kemble (reference 1) but the forms of these equations are such that general conclusions regarding the various factors affecting the exhaust process cannot be determined."

Report presenting a spectrophotometric method for identifying and estimating approximate amounts of naphthalenic-type hydrocarbons, which is suitable for finding differences in the naphthalenic content of kerosene fractions in petroleum.

From Summary: "Previous tests of blower-blade sections have been extended by a series of tests at 52.5 degrees stagger. The results of these tests have been combined with the earlier test results and are presented in new blade design charts which supersede those previously presented. An investigation in a test blower over a range of stagger from 44 degrees to 65 degrees has shown that for blades at a solidity of 1.0, the two-dimensional cascade data predict the turning angle to within 1/2 degrees."

Report presenting two-dimensional span-loading tests of a two-foot-chord NACA 65(sub 1)-012 airfoil model in the stability tunnel to determine tunnel-wall boundary-layer effects. Testing indicated that a small loss in average load may be expected. Results regarding tunnel-wall velocity profiles, pressure distributions, spanwise surveys, and force and moment coefficients are provided.

Report presenting comparisons of 24S-T aluminum-alloy flat compression panels with longitudinal Z-section stiffeners and panels with flat FS-1E magnesium-alloy sheet and longitudinal 24S-T aluminum-alloy Z-section stiffeners. The use of the composite magnesium-alloy, aluminum-alloy construction permits wider stiffener spacing with little to not loss in structural efficiency or stress for local buckling. Results regarding stiffener spacing, proportions, and consideration of the different material constructions are provided.

Research was undertaken to ascertain the properties of better wrought heat resisting alloys in the form of large discs required for gas turbine rotors. The properties of large discs of low carbon N-155 alloy in both the as-forged and water-quenched and aged conditions were determined by means of stress-rupture and creep tests for time periods up to about 2000 hours at 1200, 1350, and 1500 F. Short-time tensile test, impact test, and time-total deformation characteristics are included.

Report presenting the effects of various catalysts used to cure resinous adhesives on the strength properties of plywood, especially in regard to the degree of solidity developed by the catalysts in the resin film and the plywood. Six resins were tested with birch wood, which is the most commonly used wood in aircraft construction.

From introduction: The fundamental purpose of the laboratory is to provide research and training facilities in nuclear and related studies which are not possible for the individual University.

Abstract: The distillation and residue extraction recovery procedures developed for the recovery of uranium from Kinney and diffusion pump oil, were applied to contaminated precipitron oil. The effectiveness and advisability of using the method, in whole or in part, is discussed, and various recommendations for processing this particular type of oil are presented. Additional contaminating substances present in this type of oil added to the complexity of the problem but a satisfactory recovery procedure was, nevertheless, successfully developed.

The following report briefly covers broad general features of the chemical studies to be used by the Atomic Energy Commission in considering future work on the chemical studies of phosphate rock and shale.

Report presenting testing on a prismatic float model to determine the relationship between the vertical landing acceleration and flight-path angle for seaplanes landing in smooth water. Results regarding the maximum load factor, maximum impact normal acceleration, pressures, and stability of landings are provided.

Report presenting force tests in the 4 by 6 foot vertical tunnel to determine the aerodynamic characteristics of an NACA 0009 tapered semispan wing equipped with a plain and a balanced flap with three different included angles on the trailing edge. Results regarding lift, hinge moment, drag, pitching moment, and a comparison of calculated values with experimental values of finite-wing characteristics are provided.

Note presenting a series of tests made with a special engine equipped with a crosshead and an elastically mounted combustion cylinder. The apparatus permitted the isolation and measurement of the friction forces existing between the piston rings and the cylinder wall during operation of the engine.

A general method for studying the flow of a compressible fluid around a closed body was discussed in Part I of this report. Here, application is made to the specific case in which the linearized equation of state is used. For a given incompressible flow around a specific profile, a corresponding compressible flow is found. The flow at infinity remains unchanged. Detailed studies are made of the flow with circulation around a unit circle, and velocity distributions are found for a wide range of Mach number and angle of attack. Comparisons are made with other methods.

The feasibility of measuring the vibration in the buckets of a gas turbine under service conditions of speed and temperature was determined by use of a high temperature wire strain gauge cemented to a modified supercharger turbine bucket. A high-temperature wire strain gauge and the auxiliary mechanical and electrical equipment developed for the investigation are described.

Note presenting testing to determine the longitudinal stability characteristics with and without power of a typical low-wing, single-engine airplane model with flaps neutral, with a full-span single slotted flap, and with a full-span double slotted flap. With flaps deflected, lift increments were increased by 0.16 for the single slotted flap and 0.42 for the double slotted flap when power was applied. Results regarding lift characteristics, landing characteristics, longitudinal stability, and longitudinal control and trim are provided.

Report presenting a comparison of the maximum amount of transverse righting moment at rest provided by auxiliary floats or stub wings for 25 seaplanes and the minimum righting moment required by certain design specifications. Large differences were found to exist between the specifications and 25 designs studied.

Report presenting performance data on a helicopter rotor in flight over a range of combinations of thrust coefficient and tip-speed ratios, which included combinations intended to result in blade stalling. The study indicated that calculated angle of attack of the retreating tip should be a useful parameter for adequately defining the conditions at which stalling losses set in for a range of combinations of thrust coefficient and tip-speed ratio.