Report presenting the results of an investigation of flap-type controls on a low-aspect-ratio triangular wing using NACA 0005-63 sections for a constant-chord and a constant-percent-chord control surface. Two flap profiles were investigated: one with a true contour and the other with a blunt trailing edge. Results regarding lift, drag, pitching moment, hinge moment, and rolling moments were obtained for several Mach numbers, a constant Reynolds number, and a range of angles of attack.

The following report provides the results of an accelerated corrosion test that was performed to compare the effect of two coagulants on the corrosion rates of aluminum slug jacket alloy and 72S. Additionally, some analytical data on the water from the two treatments were obtained and are presented in this report.

This report presents "Results of a critical literature review on pressure drop due to isothermal turbulent flow in noncircular geometries" (introduction).

The following report provides measurements of the crystalline structure of neptunium metal.

The stator-blade angles in the twelfth to fifteenth stages of a 16-stage high-pressure-ratio axial-flow compressor were decreased 3 deg The over-all performance of this compressor is compared with the performance of the same compressor with standard blade angles. The matching characteristics of the modified compressor and a two-stage turbine were also obtained and compared with those of the compressor with the original blade angles and the same turbine.

Report presenting testing of JP-3 fuel and a slurry of 60 percent powdered magnesium in JP-3 fuel in a small-scale afterburner in the presence of large quantities of water vapor. The results indicated that total temperature, combustion efficiency, and air specific impulse were improved when the magnesium slurry was used, but the improvements came at the cost of increased liquid consumption.

Memorandum presenting an investigation of a 2:1 area ratio conical diffuser of length equal to the inlet diameter with separate variation of several basic parameters for simple nontwisted counterrotating rectangular vortex generators over a considerable range of inlet-boundary-layer thickness. The maximum values of static-pressure rise were determined for angle of attack, spacing, aspect ratio, and span-to-inlet boundary-layer thickness. Results for the diffuser with no vortex generators, effects of selectable vortex-generator variables, effect of inlet-boundary-layer displacement thickness, and use of the maximum indicated vortex-generator design values are provided.

From Summary: "Ogive-cylindrical fuselages of fineness ratio 11 have been flight-tested with and without stabilizing fins. Base-pressure measurements over a range of free-stream Mach numbers from 0.7 to 1.3 indicated that the fins reduced the base drag. A rear-support sting similar to those used in wind tunnels was tested with one of the fuselages and found to reduce base suction by 40 percent at subsonic speeds, but to have little effect at Mach numbers above 1.15."

Report presenting effects of wing trailing-edge bluntness on aerodynamic characteristics of a wing-body combination at a range of Mach numbers and Reynolds numbers. Modifications were made to the rear half of a basic plane tapered wing of aspect ratio 3.1 and a 3-percent-thick, circular-arc, biconvex section with three types of trailing-edge shapes. Results regarding the lift characteristics, pitching-moment characteristics, drag characteristics, and maximum lift-drag ratio are provided.

Abstract: "The amount of hydrogen normally present in zirconium and zirconium alloys suffices to reduce their ductility greatly in an impact test at room temperature, after slow cooling from 600 F. Quenching from 600 F or above gives high impact strength, as does removal of hydrogen by high-temperature vacuum annealing. This report discusses the evidence on hydrogen embrittlement, the diffusion, solid solubility, and equilibrium pressure of hydrogen of hydrogen in zirconium, the microstructure, and the effects of hydrogen and heat treatment on the mechanical properties of zirconium."

Report presenting an investigation of the effect of Reynolds number and the addition of leading-edge roughness on the aerodynamic characteristics of wings with aspect ratio 1, 2, and 3, a rectangular plan form, square-cut wing tips, and NACA 0012 airfoil sections. Results regarding lift and moment, lift-curve slope, and maximum lift are provided.

"The experimental performance of a modified turbine for driving a supersonic compressor is presented and compared with the performance of the original configuration to illustrate the effect of small changes in the ratio of nozzle-throat area to rotor-throat area. Performance is based on the performance of turbines designed to operate with both blade rows close to choking. On the basis of the results of this investigation, the ratio of areas is concluded to become especially critical in the design of turbines such as those designed to drive high-speed, high-specific weight-flow compressors where the turbine nozzles and rotor are both very close to choking" (p. 1).

Abstract: "The mechanical properties and corrosion resistance of induction-melted, zirconium-tin alloys have been determined. The alloys investigated contained from zero to five per cent tin and up to 0.3% carbon. The zirconium used was United States Bureau of Mines sponge zirconium. The mechanical properties investigated include the tensile, hot-hardness, and impact properties."

This quarterly progress report discusses ongoing work at the Metallurgy Division at the Oak Ridge National Laboratory. Topics discussed include thorium research, the preferred orientation of uranium, studies in the ceramics laboratory, the homogenous reactor program, studies in the x-ray laboratory, studies in the metallographic laboratory, the experimental plate-cladding program, and fuel and control element fabrication.

Memorandum presenting a method for calculating the stick-fixed longitudinal stability of a wing-fuselage configuration at subcritical Mach numbers. The method applies to unswept- and swept-wing configurations. The stability parameters estimated by the method show reasonable agreement with the experimental values for the 23 configurations used in the comparison.

In solving the two-group, two medium equations for neutron diffusion in a finite one-dimensional multiplying system, the equations in each medium can be solved, and the boundary conditions used to determine the coefficients. This direct attack involves eight simultaneous linear equations. The opportunities for error are numerous, and, frequently, a great deal of accuracy is lost by subtractions; hence, it is felt that an alternative method of solution, in which numerical errors would be less likely to occur, would be desirable.

A neutron burst from an untamped cylindrical Oy assembly occurred at the Pajarito Remote Control Laboratory at 1800 hours on 18 April 1952. The circumstances causing the burst and a description of the assembly involved are given There was no personnel hazard. Normal operations could have been resumed on other assemblies withing two or three hours after the burst. No evidence of damage to the oy was observed. It was determined that the burst resulted in 1.5 x 10(16) fissions in the oy. Also reported are some results of the computations and post-burst tests and a discussion of probable time behavior of power level during the burst.

Report presenting an investigation of the performance of several conical cooling-air ejectors at primary jet pressure ratios from 1 to 10, secondary shroud pressure ratios from 0.60 to 4.00, and primary to secondary temperature ratio of 1.0. The investigation centered on primary air flow, secondary air flow, primary nozzle thrust, and gross ejector thrust.

This report discusses preliminary results acquired from investigations made on the ultrasonic properties of uranium, such as sonic vibrations in the megacycle frequency range.

From abstract: "An investigation of the radiation stabilities of aqueous solutions of sodium ethylenediamine tetraacetate and sodium acetate was made using a 3000-curie Co⁶⁰ source...A study of the behavior of the standard-size Beckman type glass pH electrodes in a solution containing 0.36 curie of Ce¹⁴⁴-Pr¹⁴⁴ activity per milliliter showed the useful electrode life to be of the order of two to eight days."

The leaching behavior, thickening and filtering characteristics and recovery of uranium from high grade uranium ore from Rum Jungle, Northern Territory, Australia are described.

Memorandum presenting flutter tests of untapered, low-aspect-ratio, sweptback-wing models and of triangular-wing models of solid magnesium, aluminum, and steel construction in an intermittent supersonic wind tunnel at Mach number 1.3. Flutter data are presented for 31 sweptback wing models and 24 triangular-wing models. The flutter boundaries are indicated on plots of streamwise thickness ratio and aspect ratio.

Summary of research progress meetings of October 2 and October 9, 1952: High speed high vacuum ion pump, High energy ion irradiation, Space charge accelerator for protons, Availability of the [ ] meson beam at the cyclatron, Effect of chemical structure on stopping powers for high energy protons.

A summary of some effective aerodynamic twisting-moment coefficients of various wing-control configurations for use at a range of Mach numbers. The values obtained were determined by the combined use of experimentally determined free-flight data and subsonic aerodynamic theory.