From Summary: "A rapidly convergent successive approximation process is described that simultaneously determines both composition and temperature resulting from a chemical reaction. This method is suitable for use with any set of reactants over the complete range of mixture ratios as long as the products of reaction are ideal gases. An approximate treatment of limited amounts of liquids and solids is also included. This method is particularly suited to problems having a large number of products of reaction and to problems that require determination of such properties as specific heat or velocity of sound of a dissociating mixture."

The study of artificial radioactive isotopes is at the present time one of the most important topics in nuclear research. It involves the establishment of a detailed term scheme for the disintegration in question. Not only are the energies of the components of the different beta and gamma radiations of interest, but also their intensities. These data give information concerning the probabilities of transitions between the different nuclear energy levels. From them it is possible to draw conclusions regarding the mechanism of the disintegration and to correlate the spina and parities of the levels.

The general method of controlling the radio frequency for the full scale Bevatron will be the same as that used on the 1/4 scale machine. The details of course will be modified to meet the requirements of greater range, higher output voltage and closer tracking tolerances. In addition, there is the added complication introduced by the current ripple.

Report presenting an investigation of hot-pressed molbdenum disilicide bodies produced by industrial processes at a temperature of 2950 degrees and a pressure of 3000 pounds per square inch. Results regarding the short-time tensile strength, stress-rupture data, compression strength, air-corrosion resistance, hardness, coefficient of linear thermal expansion, thermal conductivity, and density are provided.

"Abrupt, rudder-fixed aileron rolls have been made with the Douglas D-558-I airplane (BuAero No. 37972) at Mach numbers between 0.6 and 0.89. Rolls were made at aileron deflections between one-eighth and one-half the maximum available deflection. The results obtained indicate that the aileron effectiveness is independent of Mach number and deflection within the range investigated" (p. 1).

Report presenting data gathered on a lateral-trim change or wing dropping that involves a rapid change of lateral trim with Mach number, which has occurred on several rocket-powered models used in roll investigations at transonic speeds. The data in this report demonstrates that straight wings with airfoil sections 9 percent thick or greater are susceptible to wing dropping between Mach numbers of 0.9 and 1.0. Results for straight, sweptback, and delta wings are provided.

Report presenting a theoretical analysis of the air flow through the blade coolant passages in an air-cooled turbine rotor. The simultaneous effects of area change, compressibility, wall friction, heat transfer, and rotation were included.

Report presenting the application of an estimation of the derivative of yawing moment due to rolling to the dynamic lateral stability characteristics of the Bell X-2. Results regarding the airplane with flaps and gear retracted and airplane with flaps and gear lowered are provided.

The following report provides equations that result from a seminar in reactor physics.

Memorandum presenting an investigation of the effects of compressibility on the forces, pitching moments, and surface pressures on a wing-nacelle combination. The leading edge of the wing was swept back 37.25 degrees and the nacelle was a body of revolution with a fineness ratio of 6.5. The effects of compressibility on the surface pressures and on the drag of a body of revolution similar to the nacelle were also determined.

"The results of an investigation of several internal water-inertia-separation inlets consisting of a main duct and an alternate duct designed to prevent automatically the entrance of large quantities of water into a turbojet engine in icing conditions are presented. Total-pressure losses and icing characteristics for a direct-ram inlet and the inertia-separation inlets are compared at similar aerodynamic and simulated icing conditions. Complete ice protection for inlet guide vanes could not be achieved with the inertia-separation inlets investigated" (p. 1).

The electrostatically deflected beam of the 184-inch cyclotron has been used with the stacked foil and absorber technique to determine the excitation functions. The data are presented graphically and discussed individually for each of the reactions. The results are discussed in terms of compound nucleus formation, transparency effects, and other factors in order to arrive at a qualitative picture for the mechanism of high energy nuclear reactions with heavy nuclei.

The properties of conical flow without axial symmetry are analyzed. The flow around cones of circular cross section at small angles of attack is determined by correctly considering the effect of the entropy gradients in the flow.

Technical report showing how, on a laboratory scale, a one-cycle solvent extraction process using tributyl phosphate (TBP) can be used for the recovery and decontamination of uranium 235 from spent Materials Testing Reactor fuel assemblies.

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.

Report presenting flight measurements of the aerodynamic wing normal force, bending moment, and pitching moment using strain gains on the D-558-II airplane at Mach numbers up to 0.87 and angles of attack up to 38 degrees. Results regarding Mach number effects and normal-force-coefficient effects are provided.

Report presenting an investigation in the high-speed tunnel of a 42.7 degree sweptback wing model to determine the effects of aileron trailing-edge thickness on aileron hinge moments and one-degree-of-freedom aileron flutter. Results regarding the hinge-moment characteristics and free-floating characteristics are also provided.

Memorandum presenting an investigation of the phenomenon of the starting of aerodynamic instability or buzz in supersonic inlets with external compression. The starting of the buzz has been related to the existence in the flow field of a velocity discontinuity across a vortex sheet which originates at a shock intersection. Results regarding the inlets without separation on the central body, inlets with separation on the central body, the regulation of entering volume flow at angles of attack, experimental performance of various inlets, and an application of the results are provided.

A spectrophotometric method for the determination of plutonium wing sodium alizarin sulfonate has been developed. The red plutonium-alizarin sulfonate color is developed in solutions having a pH of about three in the presence of a formic acid-sodium formate buffer, and the resulting absorption is measured at 530 millimicrons. Most interfering cations, particularly iron(III), are removed from the plutonium solutions by means of electrolysis using a mercy cathode. Aluminum(III), in quantities up to 3 percent of the plutonium content, may be tolerated in this procedure. Chloride and nitrate ions produce no interference over the concentration range studied, while tartrate, citrate, oxalate, and fluoride ions cause low results. The analysis of a large series of pure plutonium solutions, ranging from about 25 to 150 micrograms of plutonium in 10 milliliters, have a standard deviation of 0.92 percent for the determined plutonium content.

"Due to the scattered nature of existing information on the losses involved in the internal flow of gases through axial compressors and turbines, a brief survey of the available information on such losses is made. The present state of knowledge and the direction of future research toward the reduction of these losses are indicated" (p. 1).

Report presenting an investigation of 16-inch-diameter ram-jet units under free-flight conditions to determine performance at high subsonic, transonic, and supersonic velocities. Full-scale units were released from the airplane at high altitudes and accelerated by the engine thrust and force of gravity. Results regarding the diffuser total-pressure recovery, drag, thrust coefficient, and combustion are provided.

Report documenting the suitability of Arizona for plant locations to produce synthetic liquid fuels, based on raw materials, water sources, and local interest. In this report, they analyze the state primarily for coal deposits suitable for synthetic liquid fuels.

Report discusses the results of aerodynamic testing of an unswept, tapered wing with full-span, 25-percent-chord, plain, leading- and trailing-edge flaps at several angles of attack, leading-edge-flap deflection, and trailing-edge-flap deflection. This testing was done in an attempt to reduce the lift coefficients of the wings at moderate angles of attack and to provide more control for flight in the transonic Mach number range.

Report presenting aerodynamic characteristics of an unswept wing with an aspect ratio of 2.67, a taper ratio of 0.5, and employing full-span, 25-percent chord, plain, leading-edge flaps using wind-tunnel testing of a semispan model. The leading edge flap was generally effective at changing both the lift and pitching-moment coefficients at each angle of attack and Mach number. Results regarding lift characteristics, hinge-moment characteristics, drag characteristics, and pitching-moment characteristics are provided.