Abstract: "The protection of thorium in hot water was studied. Copper electrocladding on thorium offers promising protection against hot water. The corrosion of thorium in 95 C water was reduced appreciably by a thorium phosphate film. The results of this abbreviated investigation offer a basis for the development of a method of protecting thorium at elevated temperatures in corrosive media."

Technical report covering the technology of hot-pressed beryllium production and its rapid advancement toward the end of 1949. Part I is devoted to corrosion studies made on hot-pressed and vacuum cast extruded metal which was considered representative of production. Part II is concerned with the results of tests made on special cast and hot-pressed beryllium which contained added impurities. [From Introduction]

None

Memorandum reporting on TCI and other various business dealings. Details include rent, acre ownership, wells and seed planting, salary, stocks, and loans.

Weekly report discussing the state of the raw sugar market, including details for prices and market fluctuations related to weights in tons, regions, distribution, years, and figures.

Weekly report discussing the state of the raw sugar market, including details for prices and market fluctuations related to weights in tons, regions, distribution, years, and figures.

Daily cash report for Imperial Sugar Company including a list of large withdrawls for the months surrounding the date showing the daily expenses and estimated balance for each entry. It also lists scheduled payments for bank loans.

Sugarland Industries Stockholders report with information including names, certificate numbers, and shares.

Report discussing the low-speed stability and control characteristics of a modified model of the MX-1554A with a triangular wing and triangular stabilizing surfaces, which are designed to give more satisfactory stability and control than previous versions. Other modifications included an increase in slotted-flap span, redesigned tip aileron, fuselage tail cone, and speed brakes. Results provided include the effect of flow-control devices, tank and pylon location, a ground board, rotary stability derivatives, and a single support strut on the stability, control, and aerodynamic characteristics.

Memorandum presenting the application of the nuclear-reactor simulator to an investigation of the validity of the customary assumption of uniform distributions of fuel burnup and fission-product poisoning in a reactor core. The two-group calculation results show the effects of the approximation on the reactivity, power distribution, and xenon-135 distribution for a specific power reactor in which the initial power density varied by a factor of approximately 4 over the core volume.

Memorandum presenting a theoretical investigation to determine the reasons for poor airplane response to longitudinal control. Some effects of airplane configuration on the response, primarily for short time periods, were also determined. Results regarding a comparison of three airplanes, the effect of changes on airplane B, and the effect of changes on airplane C are provided.

"An investigation was conducted in the NACA Lewis altitude wind tunnel to improve the altitude performance and operational characteristics of an afterburner primarily by modifying the diffuser-exit velocity profile by changes in diffuser design and by changing the fuel distribution and the flame holder. Twenty configurations, consisting of combinations of six diffuser geometries, six flame-holder types, and twelve fuel systems, were investigated. Data were obtained over a range of afterburner fuel-air ratios at diffuser-inlet total pressures from 2750 to 620 pounds per square foot" (p. 1).

Report presenting a small-scale transonic investigation of a semispan wing sweptback 45 degrees and of aspect ratio 4 with combinations of nose-flap deflections and wing twist in the high-speed 7- by 10-foot tunnel over a range of Mach numbers. Lift, drag, and pitching-moment data were obtained for several different configurations.

Report presenting pressure measurements on a semispan model of a cambered and twisted wing, alone and in combination with a fuselage. The wing had 40 degrees of sweepback, an aspect ratio of 10, a taper ratio of 0.4, and 5 degrees of washout at the tip. Results regarding the pressure distribution and flow separation, section characteristics, and span loading characteristics are provided.

Memorandum presenting a comparison of the aerodynamic characteristics and flow phenomena at transonic speeds for a 45 degree sweptback wing mounted alternatively on a cylindrical body and an indented body. Indentation eliminated the zero-lift drag rise associated with the wing at a Mach number of 1. Results regarding the lift, drag, and pitching moment, flow surveys, level-flight characteristics, and flow phenomena are provided.

Report presenting information on the amount and relative intensity of atmospheric turbulence for altitudes up to 60,000 as obtained by airplanes and balloon-borne instruments. Analysis of the data obtained indicated that there are substantial reductions in turbulence at higher altitudes in the weather conditions measured in the tests. Results regarding gust distributions, including non-thunderstorm turbulence, thunderstorm turbulence, total gust distributions, and a comparison of gusts are also provided.

Report presenting an investigation in an altitude test chamber to determine criteria for the design of flame holders for a turbojet-engine afterburner. The performance of ten flame holders was obtained in a louvered-liner afterburner operated at constant afterburner-inlet temperature over a range of fuel air ratio and total pressures. Results regarding the effect of gutter cross-sectional shape, effect of gutter width, effect of flame-holder blocked area, effect of trailing and interconnecting gutters, and effect of altitude on V-gutter flame holders are provided.

From Summary: "Calculated velocity and temperature distributions, as well as relations among Nusselt number, Reynolds number, and friction factor, are presented. The effect of variation of fluid properties across the tube on the Nusselt number and friction factor correlations can be eliminated by evaluating the properties at a reference temperature which is a function of both the wall temperature and the ratio of wall-to-bulk temperatures."

Report presenting measurements of average heat-transfer and friction coefficients for air flowing through a smooth, electrically heated tube with a bellmouth entrance with a length-to-diameter ratio of 15 and a range of average surface temperatures, Reynolds numbers, exit Mach numbers, and heat fluxes. Results regarding the axial-wall-temperature distribution, heat balance, correlation of heat-transfer coefficients, and correlation of friction coefficient are provided.

Report presenting spanwise lift distributions, lift coefficients, spanwise centers of pressure, shifts in aerodynamic center, coefficients of damping in roll, aileron rolling-moment coefficients, and rates of steady roll per unit aileron deflection have been calculated for nine M-, W-, and delta wings, as well as for comparable ordinary sweptforward, unswpet, and sweptback wings. Certain qualitative conclusions are drawn concerning the plan forms most suitable from the aeroelastic point of view. M and W plan forms exist which are superior aeroelastically and structurally to ordinary swept wings.

Report presenting an approximate inverse impeller design procedure based on the assumption of axisymmetric, nonviscous flow along with some limited experimental data obtained from a high solidity, 12-inch transonic impeller. The design procedure includes a point-by-point solution of the impeller flow conditions along a series of streamlines in the radial-axial plane. Results regarding the overall performance, impeller flow limits, and blade structural failure are provided.

Report presenting the effects of flame-immersed blades on combustion stability and efficiency, which were determined at various combustor-inlet conditions by use of several geometric blade arrangements, two fuels, two fuel-injection systems, and two blade temperatures. Specific combustor configurations with flame-immersed blades showed marked improvement in stability and efficiency. The operational life of the blades was also observed to be excellent.

From Introduction: "An investigation of the variation in turbine-entrance equivalent weight flow for a two-stage turbine equipped with an adjustable turbine stator is presented in reference 1. A general analytical investigation of turbine stator adjustment is presented in reference 2. In reference 2, the effect of stator adjustment on turbine off-design performance is also investigated by analytically computing the performance of a particular single-stage turbine."

Memorandum presenting measurements of the oscillatory lift force acting on an airfoil vibrated in bending. Results were obtained for an isolated airfoil and for the same airfoil oscillated in a cascade, at low and high angles of attack.