Report issued by the APDA over studies conducted on reactor meltdown accidents. The studies incorporated the use of simulation materials. Methods and results of the studies are presented and discussed. This report includes tables, illustrations, and photographs.

From abstract: "Results of two methods of reducing the phosphate and vanadate contents of MgX, a uranium precipitate from the Belgian Congo, are described...Chemical analyses of several samples of pitchblende and MgX are presented."

The following report examines the most suitable enamels recommended for protection of aluminum slug cans.

Abstract: This report presents steam cycle optimization studies for large sodium graphite nuclear power generating stations.

Abstract: Pressure stress-rupture specimens of thin walled Type 304 stainless steel tubing have been tested at temperatures to 1300°F in the presence of an internal diffusion limited carbon source.

From abstract: The development, acceptance, and qualification tests performed on the SNAP-10A Ejectable Heat Shield and components, the results of those tests, and the conclusions drawn from the results are presented in this report.

From abstract: The fuel element assembly was successfully irradiated in the SRE to a maximum burnup of 5300 Mwd/MTU, at a peak fission rate of approximately 1.5 x 10E13 fissions/cm3-sec and a maximum central temperature near 1200F.

From abstract: A series of three multi-compartmented experiments was designed to investigate the irradiation behavior uranium carbide fuels, as a function of composition, temperature, and burn-up; and the mechanical properties of Type 304 stainless steel, as a function of temperature and integrated thermal neutron flux.

A method of calibrating the static-pressure source of a pitot static airspeed installation on an airplane in level flight, dives, and other maneuvers at high altitude and at transonic and supersonic speeds is described. The method principally involves the use of radar-phototheodolite tracking equipment. The various sources of error in the method are discussed and sample calibrations are included.

Report presenting a flight investigation of rocket-powered models at high-subsonic, transonic, and supersonic speeds to determine the zero-lift drag of fin-stabilized bodies of revolution differing in maximum diameter. All bodies had 6.04 fineness ratio and cut-off sterns with equal base area. The most favorable location out of the 20-percent, 40-percent, and 60-percent positions were evaluated for different speeds.

Report presenting data from 95 subsonic flutter tests conducted in the flutter research tunnel on untapered cantilever wings with sweepback angles of 0, 45, and 60 degrees and carrying a single concentrated weight. The primary purpose of the investigation was to present experimental information to be used to evaluate analytical procedures for determining the flutter speed of weighted sweptback wings. The dynamic pressure, flutter velocity, Mach number, natural and flutter frequencies, and phase-angle relationships of the stresses for the natural and flutter frequencies are presented.

A preliminary analytical evaluation of the air and fuel specific-impulse characteristics of hydrogen, a-methylnapthalene, and graphite carbon has been made. Adiabatic constant-pressure combustion flame temperatures for each fuel at several equivalence ratios were calculated for an initial air temperature of 560 degrees R and a pressure of 2 atmospheres.

A method has been developed for interpreting v-g records taken during the course of commercial transport operation. This method involves the utilization of fairly simple statistical procedures to obtain "flight envelopes," which predict that, on the average, in a stated number of flight hours, one value of airspeed will exceed the envelope, and one positive and one negative acceleration increment will exceed the envelope with equal probability of being experienced at any airspeed. Comparison with the actual data obtained from various airplanes and from various airlines indicates that these envelopes predict the occurrences of large values of acceleration and airspeed with a high degree of accuracy.

Report presenting an investigation to determine the aerodynamic characteristics of two three-blade propellers over a range of blade angles and Mach numbers. The thick-blade propeller was more adversely affected by compressibility than the thin-blade propeller, and the maximum efficiency of the thin-blade propeller was higher than the thick-blade propeller.

Report presenting a series of fence installations tested on a swept-wing jet airplane to determine their effects on the longitudinal instability, or "pitch-up", encountered in high-maneuvering flight. Longitudinal-stability measurements were made at a variety of Mach numbers with nine fence configurations that varied in chordwise extent and spanwise position. Results regarding longitudinal stability, flow phenomena, buffeting and wing dropping, drag, and low-speed stalls are provided.

"Data obtained from an extensive investigation of the cooling characteristics of four multicylinder, liquid-cooled engines have been analyzed and a correlation of both the cylinder-head temperatures and the coolant heat rejections with the primary engine and coolant variables was obtained. The method of correlation was previously developed by the NACA from an analysis of the cooling processes involved in a liquid-cooled-engine cylinder and is based on the theory of nonboiling, forced-convection heat transfer. The data correlated included engine power outputs from 275 to 1860 brake horsepower; coolant flows from 50 to 320 gallons per minute; coolants varying in composition from 100 percent water to 97 percent ethylene glycol and 3 percent water; and ranges of engine speed, manifold pressure, carburetor-air temperature, fuel-air ratio, exhaust-gas pressure, ignition timing, and coolant temperature" (p. 207).

"An experimental investigation, using microscopic observation and color motion photomicrographs of the action, was conducted to determine the cause of fretting. Glass and other noncorrosive materials, as well as metals, were used as specimens. A very simple apparatus vibrated convex surfaces in contact with stationary flat surfaces at frequencies of 120 cycles or less than l cycle per second, an amplitude of 0.0001 inch, and load of 0.2 pound" (p. 135).

"A general vector differential equation for the vorticity component parallel to a streamline is derived for steady, nonviscous, and incompressible flow in a rotating system. This equation is then simplified by restricting it to rotating radial channels and by making further simplifying assumptions. The simplified equation is used to solve for the secondary vorticity, the vorticity component parallel to the streamline, in three special cases involving different streamtube geometries; the results are presented in a series of figures" (p. 1).

Memorandum presenting the use of the hypersonic similarity rule to correlate pressure distributions and wave drags for minimum-drag nose shapes derived by Von Karman and Newton. The computed results have been confirmed by comparison with available experimental data. Wave-drag results for both the Karman and Newtonian shapes are compared with each other and with results for ocnes and circular-arc tangent ogives.

Data collected as part of a report on the Sheridan Wyoming Quadrangle including laboratory data on waters (pp. 1-22) and sediments (pp. 23-52) as well as field data (pp. 53-115).

Data collected as part of a report on the Kateel River, Alaska quadrangle including both laboratory data (pp. 1-24) and field data (pp. 25-60).

Data collected as part of a report on the Alliance Quadrangle in Nebraska and South Dakota including laboratory data on well water and stream sediments as well as field data.

Data collected as part of a report on the Raton New Mexico quadrangle including laboratory and field data on waters and sediments.

Data collected as part of a report on the Roundup Quadrangle in Montana including laboratory data on waters (pp. 1-46) and sediments (pp. 47-100) as well as field data (pp. 101-223).