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Technical report outlining cavity-type ionization chambers with graphite walls that are used to measure heat dissipation in the graphite reflector of the MTR mock-up. Studies the relationship between the ionization occurring in the chamber and the heat generated in the surrounding graphite medium. [From Abstract]

Technical report covering work completed on the removal of radioisotopes from water using a calcium phosphate floc as a carrier. This research was performed as part of the Health Physics Waste Disposal Research Section work on the removal of small quantities of radioactivity from large volumes of water. [From Abstract]

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Price Daniel, regarding a legal question submitted for clarification: Present maximum salaries of justices of the peace in Smith County.

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Price Daniel, regarding a legal question submitted for clarification: Definition of "coin-operated machine" for taxation purposes in view of possible conflict between House Bills 31 and 307, Acts 52nd Legislature.

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Price Daniel, regarding a legal question submitted for clarification: Legality of payments by Gillespie County to the Fredericksburg Volunteer Fire Department rather than to the City of Fredericksburg for rural area fire protection.

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Price Daniel, regarding a legal question submitted for clarification: Constitutionality of appropriating sums from the Available University Fund to pay county taxes on endowment lands set apart for The University of Texas.

Cost estimates for two types of Th producing plants are offered. One utilizes Th(NO3)4 as raw material, the other uses monazite sand. Final processing schemes and plant designs are not fixed, so the estimates represent maximum costs. Recommendations for research and development of Th producing methods are given.

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From Introduction: "The auxiliary apparatus described in this paper was constructed to meet this need and has been developed to a point where satisfactory measurements of relative drag can be obtained. In this paper, the apparatus is described and some comparisons are made between the results obtained with this apparatus and the measurements of free-fall, rocket, and supersonic-tunnel techniques."

Report presenting an investigation of two large-scale, semispan, wing-fuselage models with the 0.25-chord line swept back 45 degrees to determine and compare the effects of partial-span, double-slotted flaps on the characteristics of a 45 degree sweptback wing with and without camber and twist. A secondary investigation was also conducted to determine the effects of various full-span, leading-edge modifications on the characteristics of the models with and without the flaps.

Report presenting an investigation of zero-lift drag of a fin-stabilized wing-body combination from high-subsonic to supersonic speeds in a range of Reynolds numbers. The wing was unswept about the 74.5-percent-chord line, an aspect ratio of 3.04, a taper ratio of 0.394, and 4.5-percent-thick modified hexagonal airfoil sections. Results regarding total drag, wing-plus-interference drag, and base pressure are provided.

Report presenting an investigation to determine the effect of an all-movable horizontal tail on the low-speed longitudinal characteristics of a triangular-wing airplane. The model consisted of a triangular wing of aspect ratio 2, a fuselage of fineness ratio 12.5, a thin, triangular, vertical tail, and a thin, unswept, all-movable horizontal tail.

From Summary: "Physical properties of samples of three cast polyester resins known as Sierracin resins were investigated. Tests were made to determine specific gravity, index of refraction, Rockwell hardness, Tukon indentation hardness, effect of exposure to accelerated and outdoor weathering, Munsell color, resistance to accelerated service tests, crazing resistance under stress, flexural strength, Izod impact strength, and Taber abrasion resistance. Tables of the values obtained for these physical properties are included in the report."

Report presenting a comparison of the lift, drag, and pitching-moment characteristics of several wings with 35 degrees of sweepback and various amounts of camber in wind-tunnel testing. Six semispan model wings were tested, three with an aspect ratio of 10 and three with an aspect ratio of 5. Results regarding model distortion under aerodynamic loads, effects of Reynolds number, effects of Mach number, and effects of camber are provided.

The drag of a body alone, six triangular wings of various aspect ratios, and the combinations were measured at Mach numbers of 1.50 and 2.02 at a Reynolds number of 5.5 million (based on the body length). The experimental drag-interference results were in accordance with calculations based on NACA RM A9E19, 1949, with skin-friction effects taken into account, the interference effect being principally the result of fixing transition on the body by adding a wing.

The altitude-ignition limits of a condenser-discharge ignition system installed on a turbojet engine were determined at a flight Mach number of 0.6 using 1.1-pound Reid vapor pressure fuel. Ignition was possible up to an altitude of 55,000 feet with 4.8 joules per spark and 6 sparks per second.

The nature of the flow at the exit of a row of turbine blades for the range of conditions represented by four different blade configurations was evaluated by the conservation-of-momentum principle using static-pressure surveys and by analysis of Schlieren photographs of the flow. It was found that for blades of the type investigated, the maximum exit tangential-velocity component is a function of the blade geometry only and can be accurately predicted by the method of characteristics. A maximum value of exit velocity coefficient is obtained at a pressure ratio immediately below that required for maximum blade loading followed by a sharp drop after maximum blade loading occurs.

Report presenting an investigation to determine the stability and control characteristics of a vertically rising airplane model. Results of preliminary hovering flight tests are made in still air, away from the interference effects of the ground and side walls, and with normal airplane-type controls operating in the slipstream.

Report presenting testing of rocket-powered models flown at transonic speeds to determine the effect of nacelle location on zero-lift drag. Low drag was obtained between M = 0.80 and M = 0.91 for all the nacelle positions investigated. Nacelles located at the wing tips gave the lowest drag, which was less than the drag of the combination without the nacelles over most of the speed range.

Report presenting a study of a large amount of data pertaining to high-speed buffet boundaries of various airplane configurations. The data indicate a strong influence of wing configuration on buffet boundaries. Results regarding low-lift buffeting, high-lift buffeting, buffet boundaries, and buffet intensity are provided.

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In heat exchangers, in which the walls are heated by intemal heat sources, it is possible for wall temperatures greater than the mean to occur in the corners of noncircular flow Passages. Thus in a square or triangular passage low velocities occur in the corners, and the resulting decrease in the heat transfer coefficient produces higher temperatures in the walls at these locations. A generalized analysis is presented taking into account the variation in the heat transfer coefficient along the surface, by which it is possible to compute local temperatures in the walls of noncircular flow passages in the vicinity of the corners. Computations have been made for a representative component composed of a honey comb of rectangular passages. The resulting temperature at the hottest point is approximately 125 deg F greater than the unifomn plate temperature. This analysis is based on a 90 deg angle between the plate and retaining plate, and a uniforn source distribution throughout all plates. Had the angle between the primary plate and retaining plate been much less than 90 deg on both sides, then the resulting local temperature rise would be several times the above value. If the primary plate and retaining plate are …

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