From Introduction: "The single purpose of this paper is to make available the data obtained from tests of these two Clark Y section propellers as quickly as possible with no attempt being made to analyze the results or to compare them with other high-speed-propeller test results."

From Introduction: "Because of variation in the static-pressure drop across the porous material and in the cooling air required along the length of afterburner combustion chambers, a prescribed distribution of permeability is usually necessary. However, as a preliminary investigation, this report is concerned only with the attainment of uniform permeability. The results of an experimental investigation, conducted at the NACA Lewis laboratory, to determine the permeabilities of five thick meshes of wire filter cloth are presented herein."

Report presenting an altitude-chamber investigation to determine the altitude performance characteristics of the British Rolls-Royce Nene II turbojet engine with an 18.41-inch-diameter jet nozzles. Testing occurred at a range of simulated altitudes and ram-pressure ratios. Results regarding the simulated flight performance, generalized performance, and effect of jet-nozzle area on performance are provided.

An analytical investigation was made of two supersonic interceptor type airplanes to determine the most desirable turbojet engine characteristics for this application The airplanes were designed differently primarily because of the amount of subsonic flight incorporated in the flight plan--one flight having none and the other, a cruise radius of 400 nautical miles. Several power plant design variables were varied independently to determine the effect of changes in each parameter on airplane performance. These parameters included compressor pressure ratio, compressor efficiency, turbine-inlet temperature, afterburner temperature, engine specific weight, and air-handling capacity. The effects of using a convergent-divergent exhaust nozzle and of changing the design flight Mach number were also investigated.

Report presenting base pressures measured on several fin-stabilized bodies of parabolic-arc profile in free flight at a range of Mach and Reynolds numbers. The bodies varied in length but had the same afterbody ratios. Results regarding base pressure coefficients, side pressure coefficients, effect of afterbody length, and drag are provided.

From introduction: "Report of 1901 expedition of Athabaska-Mackenzie region to obtain representative collections of the mammals, birds, and plants."

An extension of the concepts advanced by Langmuir regarding the nature of the platinum catalyzed oxidation of hydrogen and the application of the resulting theory to the experimental data observed by Ranschoff and Spiewak for an HRE type recombiner indicates that their data are corrected by the dimensionless equation (see report) equally well, with a mean deviation of 3.8 percent. This expression is recommended as a basis for the design of catalytic recombiners. The catalytic combinations is pictured as consisting of two surface chemical mechanisms, one of which is oxygen diffusion controlled, the other hydrogen diffusion regulated, the mechanism "change-over" occurring at that point in the recombiner where the components are arriving at the catalyst surface by diffusion in stoichiometric proportions. The catalyst volume requirements for three two portions of the bed are shown to be (see report). The hydrogen mole fraction at the mechanism "change-over" point is (see report). And the relationship between the two mass transfer coefficients is (see report). Methods for evaluating the necessary transport properties of the ternary system steam-hydrogen-oxygen for carrying out design calculations are summarized, and the new significant parameters are tabulated and plotted to facilitate these calculations. The question of non-uniform velocity profiles …

"Determinations of the power-off maximum lift of a Fairchild 22 airplane were made in the NACA full-scale wind tunnel and in flight. The results from the two types of test were in satisfactory agreement. It was found that, when the airplane was rotated positively in pitch through the angle of stall at rates of the order of 0.1 degree per second, the maximum lift coefficient was considerably higher than that obtained in the standard tests, in which the forces are measured with the angles of attack fixed. Scale effect on the maximum lift coefficient was also investigated" (p. 161).

Results of an experimental investigation to determine downwash and wake characteristics in region of trailing vortex system behind a rectangular half-wing at Mach number 1.91 are presented. The wing had a 5-percent thick symmetric diamond cross section beveled to a knife edge at the tip. At small angles of attack, downwash angles were in close agreement with predictions of linearized theory based on the assumption of an undistorted vortex sheet. At higher angles of attack, the flow was greatly influenced by the rolling up of the vortex sheet.

Transfer operations of highly radioactive solutions by the normal transfer pipette leads in most instances to a spread of contamination in the shielded facility. In the dripless pipette, the solution is held in the reservoir by the use of the siphon principle.

The following report studies a method of assay where an unknown sample is determined by comparison with a standard sample of known isotopic ratio. The purpose is to acquaint the technical personnel with the fundamentals of the feedback method of assaying samples of TF6.

Memorandum presenting an investigation to determine the low-speed aerodynamic characteristics of a 35 degree swept-wing fighter airplane with a segmented spoiler-slot deflector lateral control system installed ahead of the conventional ailerons and operated as individual units and as combined segments. The longitudinal characteristics of the airplane and spoiler-slot-deflector effectiveness data were obtained through the complete angle-of-attack range with the ailerons neutral and with the ailerons drooped in conjunction with the normal flaps. Results regarding longitudinal characteristics, spoiler-deflector characteristics, and hinge-moment characteristics are provided.

Report presenting an investigation to determine the low-speed aerodynamic characteristics of a 35 degree swept-wing fighter airplane with a segmented spoiler-slot-deflector lateral control system installed ahead of conventional ailerons and operated as both individual units and combined segments. Results regarding longitudinal characteristics, spoiler-deflector characteristics, and hinge-moment characteristics are provided.

From Summary: "The influence of systematic variations of chemical composition on rupture properties at 1200 degrees F. was determined for 62 modifications of a basic alloy containing 20 percent chromium, 20 percent nickel, 20 percent cobalt, 3 percent molybdenum, 2 percent tungsten, 1 percent columbium, 0.15 percent carbon, 1.7 percent manganese, 0.5 percent silicon, 0.12 percent nitrogen and the balance iron. These modifications included individual variations of each of 10 elements present and simultaneous variations of molybdenum, tungsten, and columbium. Laboratory induction furnace heats were hot-forged to round bar stock, solution-treated at 2200 degrees F., and aged at 1400 degrees F."

A program has been coded for the ORACLE which will solve, using Monte Carlo technique, the transport problem for monodirectional, monoenergetic gamma radiation incident at an angle Θ, upon an infinite laminated slab of finite thickness. Each of the laminations (or regions) is itself an infinite, homogeneous slab of finite thickness. The code is designed to give estimates of energy deposition, energy flux, tissue dose rate, reflected and transmitted energy current, and the angular and energy distribution of the reflected and transmitted energy current. All the answers except for energy deposition and reflected and transmitted energy current are optional.

Report presenting testing of four delta-wing and body combinations at specified Mach numbers to determine the effect of oscillation amplitude on the damping in pitch. The body tested was the same, but the wings had 25 degree, 30 degree, 35 degree, and 45 degree semiapex angles. Results indicate that the damping-in-pitch parameter can be predicted by theory, and when a variation of this parameter with amplitude occurs, it is usually small and camping increases with decreasing amplitude.

Report presenting an investigation to determine the aerodynamic characteristics of a spoiler-slot-deflector configuration in combination with a trailing-edge 29-percent-chord high-lift flap. The wing has a sweepback of 45 degrees at the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil. Results are also presented regarding the effect of deflector projection on the aerodynamic characteristics of a spoiler-slot-deflector on the plain wing.

Abstract. Given the maximum intrinsic curvature of a rod, the maximum force required to confine it between parallel rigid walls is computed.

Summary describing research projects and other activities undertaken by the U.S. National Bureau of Standards, lists of publications from the year, and a calendar of upcoming events.

At present there are three Laboratories actively engaged in analyzing samples for the "SUNSHINE PROGRAM"; Lamont Geological Observatory, University of Chicago and the New York Health and Safety Laboratory. The U.S. Department of Agriculture Laboratories at Beltsville ae preparing samples for the University of Chicago, and are running normal strontium analyses. In order that the results reported from each of the three laboratories may be used to evaluate Sr90 distribution, a cooperative program has been in operation since August of 1953. This preliminary report lists the results on samples received and distributed by HASL. It is hoped that complete results from all laboratories will be available soon.

Introduction: "This is the ninth letter report on ARF Project C 127, entitled "Preliminary Studies of Scavenging Systems Related to Radioactive Fallout." This report covers the period from August 1 to October 1, 1959."

Report issued by the Argonne National Laboratory discussing progress made within the Reactor Development Program for September, 1966. The report includes highlights of the different project activities including plutonium utilization, fast breeder reactors, general reactor technology, advanced systems research, and nuclear safety. This report includes tables, illustrations, and photographs.

Technical report. From Abstract : "The scandium-yttrium and scandium-zirconium were studied by thermal and x-ray methods. Both systems are characterized by complete solid solubility in the low temperature hexagonal form and in the high temperature bcc form. In the Sc-Y system, there is a minimum in the solidus at 50 at. pct and 1365°C, while the solidus in the Sc-Zr system follows a nearly straight line relationship between the melting point of scandium and zirconium. There is a minimum in the temperature of transition from hexagonal to bcc in the Sc-Y system at 43 at. pct Y and 1175°C; while the temperature of transition is raised in the Sc-Zr system to a maximum of 1415°C at 30 at. pct Zr."

A set of modified NACA 65-series blower blades designed for axial inlet velocity, high inlet Mach number, and high blade loading was investigated for trailing-edge thickness of 0.015, 0.030, and 0.045 inch to determine the effect of trailing-edge thickness on single-stage axial-flow-compressor performance. Trailing-edge thickness effects were small except at the highest tip speed investigated (915 ft/sec). Trailing-edge thickness up to 30 percent of maximum blade thickness were used without sacrifice of performance of NACA 65-series blades.