Abstract: "Choline chloride and six analogs have been exposed in the dry, crystalline state to high-energy electron and gamma radiation. This investigation has confirmation the abnormal radiation sensitivity of choline chloride. Its G values (molecules decomposed/100 ev) were found to be: e- -radiation, 20; y-radiation, 175. These high values indicate a chain mechanism for the solid-state reaction. The G values for the choline analogs were found to range from 1 to 18 for the electron irradiations and from 1 to 32 for the gamma irradiations. Betaine hydrochloride approaches choline chloride in instability toward high-energy electrons but is far more stable in the presence of y-rays."

Abstract: An application of the magnetic mirror principle to the acceleration of a plasma is described. It is shown that an axially symmetric magnetic field which increases with time but decreases with distance along the axis can impart a net translational energy to a plasma. This effect on a plasma is contrasted with that arising from an impressed electric field, which is not effective in producing acceleration.

Abstract: "Probes were used to measure certain properties of the cloud of positive ions and electrons ejected from a pulsed ion source having two hydrogen-loaded electrodes. Time-of-flight measurements show: the presence of H+ ions with 50 ev directed energy; an increase of this energy with increasing pulse current in the source; a higher peak yield of ions with higher peak currents in the source; and higher yields and higher ion energies up to 110 ev have been recorded with the use of a pulsed magnetic field impressed upon the source. The neutral positive ion-electron beam from the source has been projected against an increasing magnetic field and the reflected and transmitted signals have been recorded and compared as a function of the magnetic field. Probe signals from the plasma as it encounters the magnetic field are oscillatory, suggesting that magnetohydrodynamic phenomena are presented."

The following report investigates the possible use of thermal emf's to produce the plasma-containing magnetic field in a thermonuclear reactor.

Introduction: "Prior analyses of a plasma in a magnetic field have been limited, as far as the writer is aware, to cases in which the relative change in field over the orbital distance and the relative change in ion concentration are both small, or in which the relations have been viewed in a purely hydrodynamical way. The first approach excludes cases which can be of considerable interests, for it fails near a plasma edge. The second loses all sight of the structure imposed by the orbital motions."

Abstract: The uranium occurrences near Goodsprings, Clark Co., Nevada, are divided into two distinct types which differ from each other in geographic distribution, localization of mineralization, mineralogy and origin. None of the known deposits is of present commercial significance and therefore this study emphasizes the genetic rather than the economic aspects.

From introduction: This report is based on the field and laboratory studies of the uranium mineralization in the vicinity of Goodsprings, Clark Co., Nevada. The location of the region is shown in figure 1.

"General Chemistry investigations reported herein includes: (1) the Organic Coolant-Moderator Program, (2) investigations on zirconium hydride, and (3) analytical chemistry."

Memorandum presenting an investigation of an experimental tubular combustor that provides for prevaporizing and premixing of the fuel with a part of the air before its introduction into the combustion zone. Combustion efficiency and total-pressure loss data are presented for three configurations selected from a total of 43 different modifications investigated. Results regarding the combustor development, comparison of liquid and gaseous fuel, combustor total-pressure losses, combustor-outlet temperature distribution, and evaluation of experimental prevaporizing combustors are provided.

Report presenting shock-position controls designed to actuate the translating spike and variable bypass of a variable-geometry inlet in the 8- by 6-foot supersonic tunnel. The operation of the inlet was observed in combination with a J34 turbojet engine at a range of Mach numbers. Results regarding terminal-shock-positioning control systems and combination control are provided.

Report presenting an investigation in the 9-inch supersonic tunnel to determine the jet effects for varying jet Mach number and nozzle divergence angle upon the pressure on the base annulus of a model with a cylindrical afterbody. Testing occurred over a wide range of jet static pressure ratios and Mach numbers. Results regarding sonic jets and supersonic jets are provided.

Report presenting steady straight-and-level and steady turning tracking runs against an aerial target using an F-51H airplane equipped with a fixed optical sight and with various combinations of maneuvering stick-force and stick-deflection gradients. Results regarding aim wander, elevator movement, and stick-force variation for various test conditions are provided.

Memorandum presenting an investigation in the free-flight tunnel to determine the low-speed rolling and yawing stability derivatives of a 60 degree delta-wing model from 0 to 30 degrees angle of attack. The derivatives were measured by the free-to-damp oscillation technique and by the steady-roll technique.

Report presenting lift and drag data obtained during the Douglas X-3 airplane. The data covered the Mach number range from 0.82 to 1.20 with considerable variation in lift. A comparison of the flight data with data from wind-tunnel and rocket-model tests shows that the model tests adequately predict the performance of the airplane.

Report presenting an investigation to determine the effectiveness of circulation control by applying suction through trailing-edge slots on a 45 degree sweptback wing. Various chordwise extents and depths of slot were investigated with and without deflection of a trailing-edge split flap. Results regarding the correlation of two-dimensional-section results with Ehlers' theory, effectiveness of circulation control on a sweptback wing, effect of slot configuration on circulation control, effect of trailing-edge split flap on circulation control, effect of circulation control on pitching moment, and circulation control at angle of attack are provided.

Report presents the results of an investigation of the effects of ground interference on the aerodynamic characteristics of a 42 degree sweptback wing at distances 0.68 and 0.92 of the mean aerodynamic chord from the simulated ground to the 0.25-chord point of the mean aerodynamic chord. Survey data behind the wing, both with and without the simulated ground, are presented in the form of contour charts of downwash, sidewash, and dynamic-pressure ratio at longitudinal stations of 2.0 and 2.8 mean aerodynamic chords behind the wing.

"An approximate thermal equation was derived for quenching distance based on a previously proposed diffusional treatment. The quenching distance was expressed in terms of the thermal conductivity, the fuel mole fraction, the heat capacity, the rate of the rate-controlling chemical reaction, a constant that depends on the geometry of the quenching surface, and one empirical constant. The effect of pressure on quenching distance was shown to be inversely proportional to the pressure dependence of the flame reaction, with small correction necessitated by the effect of pressure on flame temperature" (p. 1).

Note presenting the results of a survey of background and aircraft noise levels in residential communities in eight cities with major airports. The measurements were made in areas up to 12 miles away from the airports and were located in regularly used flight paths. The results indicated that there is a range of more than 20 decibels in the average background noise in the 180 areas included in the survey.

Note presenting the operating characteristics of an acceleration restrictor which limits the normal acceleration of an airplane in maneuvers determined from tests on a simulator. The simulator consisted of a control stick geared to a magnetic brake unit and an analog computer which simulated the dynamic characteristics of the airplane.

From Introduction: "These aerodynamic data were used previously in an analytical investigation of a spin recovery by rudder reversal, the results of which have been published in reference 2. Because of certain discrepancies in the rotary-balance data similar to those discussed in reference 3, some modifications were made to the aerodynamic data used in calculating the results in reference 2 and also the results in this paper; these discrepancies and modifications are discussed in detail herein."

Report presenting an approximate, theoretical analysis of the inlet or induction losses due to subsonic flow into a high-solidity cascade of finite thickness blades at incidence angle. Results indicated that the losses can become considerable for large deviations from the design incidence such as compressor off-design operating conditions. Results regarding the computational results, significance of assumptions and limitations, comparison of theoretical approximation with actual compressor results, and applicability of the results are provided.

Report presenting a theoretical and experimental investigation of heat transfer involving laminar natural convection of fluids enclosed between parallel walls oriented in the direction of body force. The results are presented in the form of equations for the velocity and temperature profiles and ratio of actual temperature drop across the fluid to the temperature drop for pure conduction.

Report presenting a systematic investigation of the sound field of a 1,000-pound-thrust solid-fuel rocket and data on two other rockets of 900 and 5500 pounds of thrust, which were obtained at a few isolated field points. Each of the three rockets was found to produce spectra somewhat similar to those of subsonic jets, which were random and with an envelope which peaks in the lower part of the audible range.

"The problem of increasing the range of supersonic aircraft by the use of twisted and cambered wings is considered, primarily for the purpose of developing a rational method for the selection of a design lift coefficient. Relations and curves are presented from which a suitable selection may be made, depending on the relative importance of maximum range and top speed" (p. 1).