Results of experimental investigation for improving intensification and to reduce stress concentrations for anvil redesign.

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.

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.

"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).

Memorandum presenting the lift, pitching-moment, and drag characteristics of a missile configuration with a body of fineness ratio 9.33 and a cruciform triangular wing and tail of aspect ratio 4 at a Mach number of 1.99 and a Reynolds number of 6.0 million. Testing was performed to investigate the effects on the aerodynamic characteristics of roll angle, wing-tail interdigitation, wing deflection, and interference among the components. Results regarding the body-wing-tail combination, body, wing and tail, body-wing and body-tail combinations, and body-wing-tail interference are provided.

Memorandum presenting an investigation conducted to reduce the pressure drop in an experimental combustor designed to operate with high efficiencies at high altitude. The combustor utilized a previously designed prevaporizing fuel system that supplied vapor fuel to the injectors for high-altitude operation. Results regarding combustor development and performance of final combustor model 47L are provided.

"An investigation has been conducted in the Langley 300 MPH 7- by 10-foot tunnel to determine the effect of negative dihedral, tip droop, and wing-tip shape on the low-speed aerodynamic characteristics of a complete model having a 45 degrees sweptback wing. Longitudinal and lateral stability characteristics were obtained for the model with and without tail surfaces" (p .1).

Memorandum presenting an investigation of the dynamics of a turbine-propeller engine in the altitude wind tunnel employing the frequency-response technique for a range of pressure altitudes form 10,000 to 30,000 feet. The investigation showed that the dynamic responses generalized for pressure altitude over the range of frequencies investigated. Results regarding steady-state characteristics, the linearity investigation, and dynamic characteristics are provided.

The effect of spark repitition rate on the altitude ignition limits of a single tubular (turbojet engine) combustor was investigated. An increase in sparking rate from 3 to 140 sparks per second reduced the ignition limiting combustor-inlet pressure about 2 to 4 inches of mercury for air-flow rates of 1.87 and 2.80 pounds per second per square foot.520::At 3.75 pounds pe At 3.75 pounds per second per square foot, the corresponding reduction was 4 to 12 inches of mercury. The trend was similar for both low-and high-volatility fuels and for two spark-energy levels.

Report presenting testing to obtain the effects of changes in Mach number, thickness ratio, and angle of attack on the amplitude of the pressure pulsations on several airfoils at transonic speeds. The tests were performed on NACA 65A-series airfoils with thicknesses ranging from 4 to 12 percent chord at a range of Mach numbers and angles of attack. The relations of pressure pulsations to buffeting are also provided.

Report discussing testing of the Douglas A-26B to determine the longitudinal stability and control characteristics. Information about the elevator, stick-fixed and stick-free stability, center of gravity, and flap effects are described.

Memorandum presenting four wings of different plan forms equipped with plain spoiler ailerons tested at low speeds. Three of the models had wings of aspect ratio 3 and different taper ratios and sweep of the quarter-chord lines, while the fourth had an aspect ratio of 4.8, a taper ratio of 0.51, and sweep of 35 degrees.

Report presenting four wings of different plan form equipped with plain spoiler ailerons tested at low speeds. Three of the models had wings of aspect ratio 3 and a range of taper ratios and sweep. The fourth model had aspect ratio 4.8 with taper ratio 0.51 and 35 degrees of sweep.

Report presenting the lift, pitching-moment, and drag characteristics of a missile configuration with a body of fineness ratio 9.33 and a cruciform triangular wing and tail of aspect ratio 4 at Mach number 1.99 and Reynolds number 6.0 million. Testing occurred over a range of angles of attack and to investigate the effects on the aerodynamic characteristics of roll angle, wing-tail interdigitation, wing deflection, and interference among the components.

Abstract: Uranium-vanadium ore has long been known in the Trachyte district. Production started in 1913 and has been erratic and intermittent to date. Until recently, practically all production from the Henry Mountains area has come from the Trachyte district.

Abstract: The possibilities for the removal of tuballoy from diffusion pump oil and reclamation of the oils for reuse are discussed. The report includes specifications of practical equipment, operating instructions, photographs and diagrams of the necessary construction details.

Report of geological investigations of the Trachyte District of the Henry Mountains in Utah

A report about anomalous low temperature thermal conductivity of grapnite samples.

A small source model for neutron flux distribution in heterogeneous reactors is proposed. Such a model takes more explicit account of fuel lumping than has been customary in most pile calculations. The small source is applied to the cases of plate and rod fuel elements. The chief results are equations which give the pile buckling in terms of the distance between fuel elements and in terms of fuel element constants. (W.D.M.)

From Introduction: "The ARMS-II Norfolk - Peninsula area survey was one many that have been flown for the CETO since the nationwide ARMS program was started (1958). Figure 2 shows the location of the areas that have been completed to date. The purpose of the program is to measure the present environmental levels of gamma radiation in areas around nuclear facilities and planned nuclear activities."

A phase shift analysis is an attempt to translate experimental measurements (observables) into well-determined scattering amplitudes, since these are the quantities that can be readily compared with theoretical predictions, In this sense, the phase shift analysis should contain as little theory as possible. The scattering amplitudes (or phase shifts) constitute an experimental statement, and the phase shift analysis should logically be done by the experimental groups who measure the observables.

Certain aspects of mating behavior in two different types of Drosophila melanogaster females (Basc and Bv) and wildtype males (Samarkand) have been investigated and compared.

Report describing the progress made in the Clinch River Study for the period May to October 1961. This report is based off of multiple reports of water sampling conducted across six stations in order to evaluate the safety and radioactive content of the Clinch River.

"Three modifications of the auxiliary-stage supercharger for the V-1710-93 engine were designed and tested as part of an investigation to improve the power output and the altitude performance of the engine. A 12-vane diffuser was substituted for the standard 11-vane diffuser, and a vaneless discharge passage and a modified scroll were designed to increase the flow capacity of the supercharger and thereby to increase the performance at the high volume flows required by the engine. With the 12-vane diffuser installed and the carburetor replaced by an adapter, the equivalent volume flow at the peak efficiency point was increased 25 percent at the lowest speed investigated and 9.5 percent at the highest speed" (p. 1).