From abstract: "The adsorption of ethane, ethylene and acetylene on clean iridium in a field emission microscope has been found to cause characteristic changes in the work function of the iridium surface. Further changes, which are time and temperature dependent, result when such surfaces are heated. Flash filament experiments have shown that the changes in work function upon heating are due to desorption reactions and that the desorbed product consists principally of hydrogen. By assuming a linear relationship between surface coverage and work function, it has been possible to determine the desorption kinetics from the observed rates of work function change at various temperatures. The results are consistent with a mechanism involving stepwise surface dehydrogenation in which a pair of hydrogen atoms is removed from the hydrocarbon molecule in each step, followed by desoption of the adsorbed hydrogen. At very high temperatures the remaining carbon atoms are removed, presumably by evaporation."

From Introduction Purpose and Scope of Report: "This report is one of a series prepared for the Research Information Center and Advisory Service on Information Processing (RICASIP), and intended as a contribution to improved cooperation in the fields of information selection systems development, information retrieval research and mechanized translation."

Report presenting a flight investigation to determine the comparative performance of AN-F-58 and AN-F-32 fuels in a 4000-pound-thrust turbojet engine. The fuels were equivalent over the range of conditions investigated. Results regarding corrected net thrust, corrected jet-fuel consumption, variation of corrected tail-pipe temperature, combustor blow-out speeds, and visual observations of the jet exhaust are provided.

Memorandum presenting a force-test investigation to determine whether the static stability characteristics of a twisted and cambered 68.7 degree delta wing could be approximated by a plane wing of similar plan form with dihedral. Results regarding longitudinal characteristics and lateral characteristics are provided.

The following report briefly covers broad general features of the chemical studies to be used by the Atomic Energy Commission in considering future work on the chemical studies of phosphate rock and shale.

Report presenting the results of flight tests conducted to determine the effect of number of fins on the drag of a pointed body moving at low supersonic velocities. The data indicated that the interference drag increased with increased number of ins up to a Mach number of 1.35, but above that value, the effect is reversed to the end of the test Mach number.

Report presenting an investigation of the effects of slot width, depth, shape, and spacing on the center-line pressure distribution in rectangular tunnels of constant cross section with several height-to-width ratios. Results are presented in the form of center-line static-pressure distributions and calculated static-pressure and angle-of-flow distributions along the slotted boundary.

Report presenting measurements of the damping in roll of cruciform triangular wings of aspect ratios 0.64, 1.28, and 2.31 at supersonic Mach numbers from 1.5 to 6.0. The models were launched from rifled guns and the time history of the model roll position in free flight was explored. Results regarding the comparison with theory, transonic effects, and comparison with results at other facilities are provided.

Memorandum presenting an experimental investigation to determine the flutter characteristics of several rectangular wings of variable aspect ratio at a range of Mach numbers. The wings were solid aluminum or steel and were 2, 4, and 6 percent thick. Results regarding the flutter at low and high angles of attack are provided.

General formulas are given for propellers for the rate of change of side-force coefficient with angle of yaw and for the rate of change of pitching-moment coefficient with angle of yaw. Charts of the side-force derivative are given for two propellers of different plan form. The charts cover solidities of two to six blades and single and dual rotation. The blade angle ranges from 15 degrees or 20 degrees to 60 degrees.

Abstract: "The heat of solution of thorium sesquisulfide was determined in 6.000 molar HCl at 25 C to ascertain the stability of the thorium (III) halides. The molal heat of formation of Th2S3 from rhombic sulfur and crystalline thorium is calculated as 258.6 kcal."

In discussion with a number of people at HAPO, KAPL and ANL a hypothesis has been evolved which appears to fit available information concerning irradiation embrittlement of uranium as well as indicate a possible solution to the problem. The purpose of this memorandum is to expound the hypothesis as an aid to those working with the problem. Since it imbodies the ideas of many people, no claim to unique authorship is implied.

Memorandum presenting testing of an experimental Custer Channel Wing airplane in the full-scale tunnel to investigate the lift characteristics of a channel-propeller combination and the flow phenomena in and about a channel wing.

From Summary: "An analytical method for calculating the aerodynamic loading on wing-tip-tank combinations in subsonic flow is developed by using a simple horseshoe vortex-image system for the case of the tank axis in the plane of the wing. An illustrative example is given in the appendix, in which wing and tip-tank loadings are calculated for three configurations. The calculated results are shown to be in good agreement with experimental data."

This is a preliminary report on a multigroup's analysis on the IBM 604, a programmable Electronic Calculating Punch, as part of the course work W31-Eng. 52.

The fabrication, irradiation and evaluation of the first two superheat fuel assemblies is described in detail. Experimental data indicate that, in general, the nuclear superheat fuel elements have performed satisfactorily under the testing conditions used. Certain problem areas which will influence future fuel element designs have been defined.

Report presenting preliminary flight-measured chordwise pressure distributions, which have been obtained at a wing midsemispan station of the Douglas X-3 research airplane through a range of angles of attack and Mach numbers. An exploration of the section aerodynamic characteristics is also provided.

"In this report tests are described in which the distribution of pressures over models of the wings of the PW-9 Airplane was investigated. The wing models were tested individually and in the biplane combination. The investigation was conducted in the atmospheric wind tunnel of the National Advisory Committee for Aeronautics" (p. 315).

Discusses history, nomenclature, common names, habits, external characters, and specimens of American marmots. Describes, lists locations, and provides a key to species and subspecies.

Abstract: Fifty-four spectral lines of curium are listed together with estimated intensities. A brief description of the manner of taking the spectra and of measuring the lines are given.

Report presenting a theoretical study of certain anomalies in the behavior of a ram-jet engine engine tip-mounted on a rotating helicopter blade that appears to be related to centrifugal effects distorting the fuel-spray pattern. Results regarding the cases calculated, results of the calculations, particle-path distortion, and limiting direction of particle paths are provided.

Report presenting some equations that give the interference on the trailing-vortex system of a uniformly loaded finite-span wing in a circular tunnel containing partly open and partly closed walls, with special reference to symmetrical arrangements of the open and closed portions. Methods are given for extending the equations to include tunnel shapes other than circular.

Thesis discussing the heats of reduction, oxidation potentials, and measurements of autoreduction and disproportionation for aqueous ions of americium.

From Summary: "The results of force tests made at low speed are presented to show the effect of longitudinal static stability produced by drooping the tip of a 63 degree sweptback wing. Five semispan wing models were tested: two incorporated curved drooped tips, two with abruptly drooped tips, and one without droop. The most favorable stability characteristics were measured for a model with an abruptly drooped tip, a fence, and a leading-edge flap; however, the use of these same auxiliary devices on the undrooped wing was nearly as effective."