The following report studies an estimation of the amount of Pu(III) and Pu(IV) present in the IBP Stream, with the purpose of establishing an analytical, method suitable for routine control analysis. A method is discussed that is based on carrying Pu(IV) upon a zirconium phanylarsonate precipitate.

This technical report provides supplementary information on the Brookhaven nuclear reactor. It details added safety systems, tests, expounds on information included in the original report, describes liquid wastes system, and describes different procedures for operating the nuclear reactor.

Report presenting the results of an investigation to determine the effect of Mach number on the aerodynamic characteristics of a flying-boat hull with a high length-beam ratio. Information about the drag coefficients, angles of attack for minimum drag, and longitudinal and directional stability is provided.

Report presenting an extensive collection of lift and hinge-moment characteristics of control surfaces up to a Mach number of 0.90 in a high-speed wind tunnel. A wide variety of control-surface profiles, plan forms, and aerodynamic balances are included. Results regarding elevator hinge moments and longitudinal control, aileron hinge moments and lateral control, control-surface characteristics, and transonic flutter are highlighted.

Memorandum presenting an investigation conducted to determine experimentally turbine-nozzle-blade and turbine-bucket temperatures in a turbojet engine and to correlate these temperatures with the gas temperatures. Data were obtained over the normal range of engine speeds and with two tail-pipe-nozzle areas. Results regarding basic data, turbine-nozzle-blade temperature distribution, turbine-bucket-temperature distribution, temperature distribution of gas at burner-outlet, turbine-bucket temperatures during starting, and relation of material and gas temperatures are provided.

Report presenting the operational characteristics of a 20-inch ramjet with four different gutter-grid flame holders and a three-gutter flame holder with an adjustable gutter angle. The flame holders were compared on the basis of operating ranges of fuel-air ratio, combustion-chamber-inlet velocity, and the combustion efficiencies obtainable.

Report presenting an investigation to determine the maximum quantity of water that could be injected either into or ahead of a single can-type combustor without reducing the attainable combustor-outlet temperature below the value required for engine operation and without the appearance of liquid water at the combustor outlet. Water was injected from spray nozzles at four different stations along the combustor.

Report presenting a method for applying the limited contraction ratio to obtain the maximum allowable blade thickness of a two-dimensional model of a supersonic-compressor rotor.

Report presenting a flight and wind-tunnel investigation to determine the aerodynamic vibration characteristics of ailerons for the Douglas D-558-2 airplane. Testing was conducted to investigate the possibilities of a single-degree-of-freedom flutter known as aileron "buzz" or aileron compressibility flutter. Results regarding the three types of aileron vibration observed and vibration amplitudes are provided.

Report presenting a wind-tunnel investigation using the transonic-bump method to determine the longitudinal stability and control characteristics of a semispan airplane model with a 45 degree sweptback wing and tail at transonic speeds. An increase in the rate of change of the pitching-moment coefficient with lift coefficient at a constant Mach number through the transonic range was noted.

Memorandum presenting an investigation conducted to study the performance of a single-stage axial-flow compressor using blades with an NACA 5509-34 airfoil section. Static- and total-pressure, total-temperature, and flow-angle surveys were taken in the compressor inlet and outlet and between blade rows to study the overall performance and individual blade-row performance.

Memorandum presenting a wind-tunnel investigation made in the stability tunnel to determine the effects of lift flaps on the static lateral stability derivatives and the yawing derivatives of an untapered 45 degree sweptback wing at low speeds. Results regarding straight flow and yawing characteristics are provided.

"Vibration investigations were made of two blade cascades in wind tunnels and of blades operated in the NACA 24-inch supersonic compressor. The results showed that the blade vibrations were present at all tunnel and compressor air velocities and were influenced primarily by tunnel design, simulated centrifugal loading, surging, angle of attack, and possible critical Mach numbers" (p. 1).

Report presenting an investigation to determine the characteristics in yaw of a trapezoidal wing of aspect ratio 4 with circular-arc airfoil sections and 0.20-chord rear and drooped-nose flaps. Measurements of lift, lateral force, rolling moment, and yawing moment of four configurations were made for a range of angles of attack and yaw angles.

The investigation includes steady and accelerated vertical and longitudinal motions and steady rolling, yawing, sideslipping, and pitching for Mach numbers and aspect ratios greater than those for which the Mach line from the leading edge of the tip section intersects the trailing edge of the opposite tip section. The stability derivatives are derived with respect to principal body axes and then transformed to a system of stability axes. Theoretical results are obtained, by means of the linearized theory, for the surface-velocity-potential functions, surface-pressure distributions, and stability derivatives for various motions at supersonic speeds of thin flat rectangular wings without dihedral.

Report and corollary maps on the Eurida (Toh Atin) District, Carrio Uplift, Arizona.

The following report is a quarterly report done by the Physics Division of the University of California's Radiation Laboratory, covering the period of February 1, 1948 to May 1, 1948. This report discusses general physics research and the development and operation of the accelerator.

Construction of a linear accelerator which increases the energy of protons from a 4 Mev Van de Graaff injector to a final energy of 31.5 Mev.

From Summary: "A 19XB-1 combustor was operated under conditions simulating zero-ram operation of the 19XB-1 turbojet engine at various altitudes and engine speeds. The combustion efficiencies and the altitude operational limits were determined; data were also obtained on the character of the combustion, the pressure drop through the combustor, and the combustor-outlet temperature and velocity profiles. At altitudes about 10,000 feet below the operational limits, the flames were yellow and steady and the temperature rise through the combustor increased with fuel-air ratio throughout the range of fuel-air ratios investigated. At altitudes near the operational limits, the flames were blue and flickering and the combustor was sluggish in its response to changes in fuel flow."

From Introduction: "The particular blade design, the tests of which are described in the present paper, was one necessary to the investigation of the effect of differences in blade-thickness ratios."

"The NACA is investigating a series of J-33 turbojet-engine compressors to determine the over-all and component performances and to improve theories of flow through large centrifugal compressors, The production model J-33-A-21 was operated over a range of inlet temperatures from 80 to -40 F and inlet pressures from 14 to 5 inches mercury absolute for equivalent impeller speeds from 6000 to 13,400 rpm. At the equivalent design speed of 11,500 rpm, the compressor had a peak pressure ratio of 3.98 at an equivalent weight flow of 73.4 pounds per second and an adiabatic temperature-rise , efficiency of 0.701" (p. 1).

Report discussing an investigation of the low-speed characteristics of a wing with a triangular plan form, 60 degrees of sweepback at the leading edge, and 10-percent-thick biconvex airfoil sections. The purpose of the investigation was to determine the effects of semispan and full-span leading-edge and trailing-edge flaps on the longitudinal aerodynamic characteristics of the wing and the effects of a vertical fin on the lateral stability characteristics.

"With the assumptions that Berthelot's equation of state accounts for molecular size and intermolecular force effects, and that changes in the vibrational heat capacities are given by a Planck term, expressions are developed for analyzing one-dimensional flows of a diatomic gas. The special cases of flow through normal and oblique shocks in free air at sea level are investigated. It is found that up to a Mach number 10 pressure ratio across a normal shock differs by less than 6 percent from its ideal gas value; whereas at Mach numbers above 4 the temperature rise is considerable below and hence the density rise is well above that predicted assuming ideal gas behavior" (p. 239).

"A method for calculating the flow fields of axially symmetric bodies from their pressure distributions is reported in NACA RM No. L8I17. In order to facilitate application of this method to the important case of the cowling-spinner combination, for use in the design of propellers, the present paper presents static-pressure distributions on the tops of 79 high-critical-speed NACA 1-series cowling-spinner combinations over wide ranges of inlet-velocity ratio at angles of attack of 0 degrees, 2 degrees, 4 degrees, and 6 degrees. Static-pressure distributions around the nose sections of several cowlings are given in greater detail to aid in estimating the pressures near the stagnation points and to show the effect of changes in the internal lip shape" (p. 1).