Results regarding an investigation to determine the horizontal- and vertical-tail contributions to the static lateral stability of a complete-model swept-wing configuration at high subsonic speeds. Generally, Mach number effects within the range studied and wing effects on the tail contribution were small and the overall trends of the data of the present investigation agreed with those which have been established at low speeds.

Abstract: "The solubility of oxygen in uranyl sulphate solutions and in water at 212, 275, and 325 F, and at oxygen partial pressures up to 1500 psia was investigated. The results are presented in tabular and graphic form. The solubility is proportional to the partial pressure of oxygen. The ratio of solubility in the uranyl sulphate solution to solubility in water at the same temperature and pressure is a function of the concentration of the salt in solution."

Abstract: "A completely Lagrangian scheme for differencing hydrodynamical equations in two dimensions is described. The method conserves mass exactly. The advantages of Lagrangian over Eulerian schemes are briefly mentioned. An appendix gives the generalization to three dimensions."

This report discusses the production of plutonium metal through the reduction of plutonium tetra fluoride with calcium metal and sulfur. It elaborates that iodine, which was originally used instead of calcium metal, presented several practical problems, but reductions completed with calcium were unsatisfactory.

Six determinations have been made of the half life of polonium with four different steady-state, resistance-bridge calorimeters and five different samples of polonium. These six values of the half life have been weighted and combined to give a grand-mean value of the half life of 138.4005 + - 0.0051 days.

Weekly report discussing the state of the raw sugar market, including details for prices and market fluctuations related to weights in tons, regions, distribution, years, and figures.

List of shares for various people.

Weekly report discussing the state of the raw sugar market, including details for prices and market fluctuations related to weights in tons, regions, distribution, years, and figures.

The relative probabilities for alternate processes initiated by a nucleon-nucleon collision depend on the dynamics involved and on the volume in phase space accessible to each final state. According to Fermi this last aspect alone may be of decisive importance. Such an assignment would follow were an approximate statistical equilibrium reached. The volume occupied by the incident nucleons and the associated pion clouds will have very large energy density at the instant of collision. Knowing that the interactions of the pion fields are strong, Fermi assumes that this energy is suddenly distributed among the various degrees of freedom present in the interaction volume in accord with statistical laws. He then computes the statistical probability that a certain number of pions will be created with a given energy distribution. It is then assumed that the energy will rapidly dissolve and that the particles into which the energy has been converted will fly out in all directions. Fermi argues that this approach may give a fairly good approximation to the actual case; since the number of possible states of the given energy is large and the probability of establishing a state to its average statistical weight will be increased by the number …

None

None

None

None

None

Daily cash report for Imperial Sugar Company including a list of large withdrawals for the months surrounding the date showing the daily expenses and estimated balance for each entry. It also lists scheduled payments for bank loans.

"Calculations have been made to determine the effects of Mach number and altitude on the lateral frequency response, the lateral response to a lateral sinusoidal gust distribution, and the period and damping of the lateral oscillation for the North American F-86A, Grumman F9F-2, Republic F-84, Douglas D-558-II, and Bell X-1 airplanes without autopilots. Aeroelastic and unsteady lift effects have not been included in the calculations and may have a large effect on the results for certain flight conditions. The results of the investigation are presented, without analysis, for reference purposes" (p. 1).

Report presenting two-group criticality calculations for sodium-hydroxide-cooled, moderated, and reflected reactors for various concentrations and compositions of reactor fuel-element structural material. The investigation was performed in order to determine the applicability of the fuel properties to power a nuclear aircraft. Results regarding the specific reactor calculations, reflector savings, criticality generalization, typical neutron flux and heat-generation distributions, static stability characteristics and excess uranium requirements, reactor heat-transfer characteristics, and airplane and turbojet cycle characteristics are provided.

Report presenting results of two-group criticality calculations for sodium-hydroxide-cooled, moderated, and reflected reactors for various concentrations and compositions of reactor fuel-element structural material. Based on turbojet-engine cycle operating conditions optimized for minimum airplane gross weight, the maximum reactor fuel-element and coolant temperatures are related to the reactor heat release and airplane gross weight for a range of reactor heat-transfer variables.

Report presenting an investigation to determine the performance characteristics of a double-shroud cooling-air ejector configuration. Two convergent nozzles were used to simulate a specific manufacturer's iris-type variable-area nozzle in the open and closed positions. The investigation had four phase: (1) obtaining performance with no secondary or tertiary air flow, (2) determining the tendency for backflow to occur in either cooling-air passage, (3) determining the sensitivity of flow in one passage to the other, and (4) obtaining pumping and thrust characteristics with secondary and tertiary air flow.

Report presenting some measurements of the dynamic lateral stability and lateral and longitudinal trim of a Douglas D-558-II in flights up to a Mach number of 1.87 and an altitude of about 67,000 feet. Testing indicated that the airplane flying in low density air at supersonic speeds had poor dynamic lateral stability, which worsened as the Mach number was increased to 1.85.

From Summary: "An analytical investigation was made to determine from component performance characteristics the effect of air bleed at the compressor outlet on the acceleration characteristics of a typical high-pressure-ratio single-spool turbojet engine. Consideration of several operating lines on the compressor performance map with two turbine-inlet temperatures showed that for a minimum acceleration time the turbine-inlet temperature should be the maximum allowable, and the operating line on the compressor map should be as close to the surge region as possible throughout the speed range. Operation along such a line would require a continuously varying bleed area."

Memorandum presenting an investigation of the effects of longitudinal location of the wing and varying body size on the interference characteristics of a 45 degree sweptback wing over a range of Mach numbers and angles of attack. The wing had an aspect ratio of 4, a taper ratio of 0.6, and NACA 65A006 airfoil sections. The results indicated that the zero-lift drag of the wing with interference in the forward position was lower throughout the Mach number range than for the wing with interference in the rearward position.

Memorandum presenting an investigation made of the effects of store mounting on the buffet, trim, and drag characteristics of fuselage-mounted external stores between Mach numbers of 0.7 and 1.4 by the use of the rocket-propelled-model technique. Results of the tests are presented in the incremental accelerations in the stores due to buffeting, trim normal- and side-force coefficients, tail helix angles, and drag coefficients plotted against Mach number.

Report presenting an investigation of systematic series of sharp- and blunt-trailing-edge wings to determine the effects of thickening the trailing edges on the lift, drag, and pitching moment characteristics at several Mach numbers. Results indicate that no appreciable zero-lift drag reduction can be obtained by thickening the trailing edges from 1.41 to 1.96, but trailing edges can be thickened appreciably with no increases in zero-lift drag.