This monthly document details activities of the Hanford Operations Office during the month of March 1959. (FI)

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Memorandum presenting a determination of the static lateral stability of six delta wings at subsonic speeds. In addition, two of the wings with 82.5 degree and 75 degree sweep of the leading edge were oscillated in yaw about the 50-percent point of the root chord in order to determine the effects of frequency and amplitude on the combination lateral stability derivatives resulting from the motion. Results regarding the static characteristics and oscillatory characteristics are provided.

Report presenting an investigation to determine the control hinge-moment characteristics at two Mach numbers for a series of 18 controls, including the effects of various tabs and fences, on a 60 degree delta wing. Testing covered a range of angles of attack, control deflection, and tab deflection. Results regarding the basic variation of hinge-moment coefficients, tip controls, and trailing-edge controls are provided.

Report presenting detailed blade-element-performance plots for a high-flow transonic inlet rotor. Information provided includes the effects of Mach number, blade loading, and angle of attack on element performance is provided.

Report presenting an investigation at Mach numbers from 0.6 to 1.28 to determine the drag characteristics of a series of conical afterbodies with a cold sonic jet issuing from the base. Models investigated had boattail angles from 3 to 45 degrees, ratios of jet diameter to base diameter of 0.65 and 0.75, and values of the ratios of the base diameter to maximum diameter of 0.55, 0.70, and 0.85. Results regarding afterbody pressure distributions and afterbody drag are provided.

Report discussing a project to determine a high-energy fuel suitable for turbojet-powered aircraft. Components of the project include thermal and combustion properties, experiments with combustors using boron compounds, evaluation of boron fuels in full-scale turbojets with and without afterburners, and boron fuel use in ramjet flights. The most promising fuel found in the report is pentaborane.

Report presenting NACA work through 1954 on a high-energy fuel suitable for turbojet-powered aircraft. The work includes thermal and combustion properties, experiments with combustors designed to use boron compounds, evaluation of boron fuels in full-scale turbojets with and without afterburners, and ramjet flights on boron fuels. Satisfactory combustion of pentabornae and high-concentration blends of pentaborane has been demonstrated in a turbojet, an afterburner, and a ram jet.

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This report addresses the analyses for fission-product antimony-125 made on samples of selected Thorex streams. The results are summarized in Table I

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Various methods were investigated to produce a heater tube fuse. Utilizing powder metallurgy techniques, fuel tubes with an I.D. of 0.045 inch, O.D. of 0.075 inch, and length of 11/16 inch, containing various compositions of copper + UO/sub 2/, were fabricated. Fabrication methods consisted of compacting the tubes in quarter-length units, sintering under optimunn conditions, coining on a tinplated inner tube with tin washers between units, and then heat treating to obtain a proper bond. By these techniques, 33 unis containing various compositions of copper + U/sup 235/O/sub 2/ were fabricated and shipped to Atomics International for testing. In addition, work was performed on the brazing facet of the trigger element assembly, joining the copper + UO/sub 2/ fuel tube to a type 347 stainless steel thermal resistance pad and block. (auth)

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Critical mass, fuel concentration, power, maximum power density, and wall power density were obtained for bare spherical reactors having diameters of 8, 10, 11, and 12 ft, operating at 20, 100, 2OO, and 300 deg C. (L.T.W.)

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Two types of ``feedstock,`` i.e. irradiated uranium and uranium from underground storage, are processed by the 200 Areas. Future operations may add irradiated thorium as a supplementary feed material. In either case, the major portion of future feedstocks is presumed to be in the form of irradiated metal, i.e. uranium and/or thorium, resulting in an almost complete dependence of the required 200 Area processing rate on reactor power levels and metal irradiation history. This document presents correlations by which predicted reactor power levels and production commitments for particular types of product may be easily converted to the required separations processing rates. Separations processing rates potentially resulting from low NGS plutonium and ``23`` commitments are given for the period through 1957.

From Introduction: "The purpose of the present report is to present a comprehensive summary of theoretical investigations of comprehensible laminar boundary layers which have been carried out since 1949 at the Polytechnic Institute of Brooklyn under the sponsorship and with the financial assistance of the National Advisory Committee for Aeronautics. The results of these investigations are contained primarily in references 1 to 7."

Buckling measurements were taken with hollow natural uranium slugs in graphite-moderated lattices, in which the lattice spacing was varied from 6 3/16 to 15 inches in five steps. A 1.66" O.D. slug was used with two different core sizes, 1.11" I.D. and 0.81" I.D. The results of wet (water in the core) and dry measurements are reported. Buckling curves are given showing the effect on the buckling of coring the slug and placing water in the core. Simple three-region diffusion theory is applied to the measured lattices in an effort to correlate measurement with theory, but with only limited success.

This memorandum indicates the Purex-Plant pulse-column and pulse- generator revisions which would be required to assure an instantaneous capacity of 25 tons U/day with a 20% capacity safety margin under Purex HW {number_sign}3 Flowsheet conditions. (The use of the Purex HW {number_sign}4 Flowsheet (6) with the revised columns would be expected to increase the capacity to 29 or 30 tons U/day.) The indicated design changes are recorded here for study and for possible reference if need for increased production capacity should arise. No recommendation for adoption at this time is made.

Report presenting an investigation to determine the aerodynamic characteristics of a cruciform 70 degree delta-wing missile configuration with 70 degree delta canard control surfaces at M = 1.41 in the 4- by 4-foot supersonic pressure tunnel. Modifications to the configuration included variation of the body length and canard area and the substitution of a series of very small span wings for the cruciform delta wings and canard controls.

Report discussing an investigation to determine the effects of aeroelasticity on the rolling effectiveness of a model of a McDonnell F3H-1 airplane wing. The plane was found to be subject to aeroelastic losses that varied with Mach number and altitude.

Report presenting an investigation to determine the effects of aeroelasticity on the rolling effectiveness of an 8.06-percent-scale model of the McDonnell F3H-1 airplane wing. The investigation used rocket-propelled models in free flight over a range of Mach numbers. The results indicate that the airplane is subject to aeroelastic losses varying from about 7 percent at Mach number 0.5 to 46 percent at Mach number 0.90 at sea level.