This report discusses a system which has been conceived whereby additional flexible reactivity control in the production reactors can be achieved by introducing neutron absorbers contained in thin flexible metal strips between the slugs and the process tube wall. These splines are potentially attractive in that it is possible they could be used to provide additional flexible control during operation as well as temporary control during outages.

The operation of a Priest Rapids dam is stated to necessitate river flow manipulation varying from 25,000 cfs to 120,000 cfs in the winter months of a critical water year. The low flow may persist for periods of six hours daily, and the expected daily average low flow is 61,000 cfs. The possible effects of this on reactor operation and waste disposal to the Columbia River which are of the interest to the Radiological Sciences Department were reviewed by J.F. Honstead, R.E. Rostenbach, and R.F. Foster. These include radiation hazards in reactor area water treatment plants, reactor area drinking water contamination; increased river temperature; chromium pollution problems; effects on downstream river usage, and effects on aquatic life.

Travel to Battelle Memorial Institute to discuss the results of subcontract research on the extended surface fuel element program and to review progress on the consolidation of Horizons` electrolytic thorium. Nickel-plated uranium samples, press-clad with 30-mil thick aluminum at 6, 10, and 15 thousand psi, have been on corrosion test for periods of 10 to 31 days. Six specimens from the 6,000 psi group have failed by undercutting after 21 to 31 days; this is another good record. Pinch welds have proved very effective as a means of sealing corrosion samples. Two 9--10 pound virgin ingots and three smaller remelts were made by consumable electrode arc melting of Horizons` electrolytic thorium. Physical and chemical data on the remelts are being obtained. Diffusion coefficients have been determined, at two sets of time-temperature conditions, for two diffusion couples of aluminum and a 0.5 w/o thorium in aluminum alloy, after high temperature annealing. The data show that the rate of interdiffusion of thorium and aluminum is very slow. These results are discussed.

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Report presenting free-flight measurements of the rolling effectiveness and drag of trailing-edge spoilers on low-aspect-ratio wings with both laminar and turbulent boundary layers at two different Mach numbers. The effect of a spoiler deflected from the surface of a wing is to cause boundary-layer separation upstream.

Boundary-layer transition data at low ratios of wall to local stream temperature have been obtained during the free flight of a highly polished cone-cylinder to a maximum Mach number of 5.02 A maximum transition Reynolds number of 32 x 10(exp 6) occurred at a distance of 25.84 inches from the cone apex. The temperature ratio at transition for a local Mach number of 4.0 was approximately 1.30 as compared with theoretical infinite stability solutions of 1.47 and 1.65 by Dunn and Lin (three-dimensional) and Van Driest (two-dimensional), respectively.

"The zero-lift drag of a 1/7-scale model of the Convair B-58 external store was obtained at mach numbers between 0.8 and 2.45 at corresponding Reynolds numbers per foot of 3.5 x 10 to the 6th power and 15.3 X 10 to the 6th power. The experimental drag data are compared with calculated values at both subsonic and supersonic speeds and show good agreement. In addition to the drag data, some static stability derivatives and damping factors were also obtained and are presented with the predicted values of these derivatives for completeness and for comparison" (p. 1).

Report presenting measurements of recovery temperatures on a slender cone-cylinder with a 12 degree vertex angle and a 1.25-inch-diameter cylinder for a range of Mach numbers. Results regarding the visual evidence, temperature distributions, pressure distributions, summary figures, correlation of temperature patterns with boundary-layer transition and separation, and recovery factors are provided.

The presence of 3 to 5 percent surface-active additive gave the lowest Brookfield apparent viscosity, plastic viscosity, and yield value that were obtained for slurry fuels containing approximately 50 percent vapor-process magnesium in JP-1 fuel. The slurries settled little and were easily remixed. A polyoxyethylene dodecyl alcohol was the most effective of 13 additives tested in reducing the Brookfield apparent viscosity and the yield value of the slurry. The seven most effective additives all had a hydroxyl group plus an ester or polyoxethylene group in the molecule. The densities of some of the slurries were measured.

The magnitude and variation of the static-pressure error for various distances ahead of sharp-nose bodies and open-nose air inlets and for a distance of 1 chord ahead of the wing tip of a swept wing are defined by a combination of experiment and theory. The mechanism of the error is discussed in some detail to show the contributing factors that make up the error. The information presented provides a useful means for choosing a proper location for measurement of static pressure for most purposes.

A study of mixtures of pure methanol and trimethyl borate showed that the composition can be accurately obtained by a simple density determination. The refractive-index determination gives the composition with much less accuracy. The potentiometric titration of boric acid is also discussed.

Report presenting a technique and the results obtained of wind-tunnel forced-oscillation tests on a model of the Douglas D-558-II airplane which was instrumented to obtain the dynamic cross derivative and static derivative. Tests were conducted for a range of Mach numbers and angles of attack. Results regarding sample calculations of the period and damping of the full-scale airplane are provided despite not being conclusive due to the inadequate number of flight conditions investigated.

A compilation of the six technical papers presented at the NACA Conference on Engine Stall and Surge on February 3, 1955 at the Lewis Flight Propulsion Laboratory. A list of conference attendees is also provided.

Report presenting testing of a body with a 22.5 degree conical nose, a 4-diameter-long cylindrical midsection, and a 20 degree cone-frustum tail flare. The tests were made over a variety of angles of attack and Mach numbers. Results regarding spark shadowgraph pictures and predictions versus the actual values were provided.

Report presenting a method for analyzing each of the elements, boron, carbon, and hydrogen from the quantitative analysis of a single sample of an organoboron compound. The method is helpful for the analysis of volatile hydrocarbons and polynuclear aromatic compounds.

From Summary: "An experimental wind-tunnel investigation was conducted at Mach 1.9 to determine the pressures acting on the base of a multijet missile using unheated air and carbon dioxide as jet fluids. The variation of base pressure with jet static-pressure ratio was compared with results estimated for an axisymmetric single-jet model and some correlation was observed."

Memorandum presenting an investigation of the effective thermal conductivities of powders, which included uranium oxide UO(sub 2) powder with a density of 59.5 percent of the density of the solid uranium oxide at a range of temperatures. Helium, argon, and nitrogen gases and mixtures of helium-argon and xenon-krypton gases were introduced into the powder void, and the experimental effective thermal conductivities of the gas-powder mixtures were determined.

Report presenting an experimental investigation to determine the internal performance characteristics of a series of circular, open-nose auxiliary air inlets immersed into the supersonic, turbulent boundary layer generated by the 8- by 6-foot supersonic wind tunnel. Inlet critical total-pressure and mass-flow ratios were reasonably predicted by theory at all conditions investigated. Results regarding boundary-layer flow, inlet performance, and diffuser-exit pressure fluctuations are provided.

Report presenting a correlation of the available data on various flap-type high-lift devices in two-dimensional form for flap-chord ratios ranging from 20 to 40 percent. Data for plain, single-slotted, and double-slotted flaps, and for suction and blowing flaps, are provided. Analysis regarding the effect of wing thickness and slot width is also provided for the various types of flaps.

Report presenting an investigation of the effectiveness of transpiration cooling on an 8 degree total-angle conical body with a porous skin for various coolant mass flow rates of nitrogen gas, helium gas, and distilled water.

Report presenting seven pairs of wings tested at Mach numbers of 1.63, 1.93, and 2.41 to determine the validity of NACA TN 2858, which predicts that delta wings with linearly varying thickness ratio have less wave drag than a constant-thickness-ratio delta wing. Results regarding the zero-lift wave drag, values of lift, total drag, pitching moment, and lift-drag ratios for an angle of attack range are provided.

Performance characteristics of four hydrocarbon fuels having high Btu per gallon were determined in a single turbojet combustor. At simulated low-altitude operating conditions, the fuels with high Btu per gallon generally produced more carbon than did JP-4 and JP-5 fuels. The deposits were reduced appreciably with a fuel-oil additive. At high-altitude conditions, the high Btu-per-gallon fuels gave lower efficiencies than did JP-4 or JP-5 fuels. No attempts were made to improve performance by combustor design modification.

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