Report presenting an investigation to measure the flying qualities of a high-performance personal-owner airplane to investigate the possible causes of instrument flying accidents with that type of aircraft. Testing indicated that the lack of aerodynamic stall warning and rapid roll-off at the stall could contribute to stall-spin accidents with high-performance personal-owner aircraft. Results regarding the handling qualities and the control under instrument flying conditions are provided.

Since the 25 content of the uranium to be used in a MTA multiplying lattice is quite uncertain at present, it is necessary to assume various degrees of depletion in order to estimate the multiplication constant K-o and the production of 49 in an infinite uranium-graphite lattice

A series method of determining two-dimensional vortex paths is considered and applied to the computation of vortex positions behind a slender equal-span cruciform wing at any angle of bank as a function of the distance behind the trailing edge. Calculated paths are shown for four bank angles. For a bank angle of 45 degrees comparison is made with the results of a closed expression given in NACA-TN-2605. For other bank angles water-tank experiments provide qualitative comparison. Satisfactory agreement is found for a sufficient distance downstream to include most practical missile-tail positions. The interference forces on an equal-span cruciform wing are calculated for five angles of bank (including the trivial case of zero bank) from the vortex positions found by use of the series.

Report presenting an investigation of the pumping characteristics of eight conical ejectors mounted on a fuselage portion of a supersonic airplane. The diameter ratio, spacing ratio, nozzle pressure, and ejector weight flows were varied. Results regarding the ejector pumping characteristics, comparison with previous results, comparison of data for cold and hot primary flow, and ejector air-supply requirements are provided.

Report presenting an investigation of the pumping characteristics of eight conical ejectors mounted on a scale fuselage portion of a supersonic airplane. The configurations simulated various positions of a two-position nozzle with a fixed shroud and double-iris exit. Results regarding ejector pumping characteristics, comparison with previous results, comparison of data for cold and hot primary flow, and ejector air-supply requirements are provided.

Zirflex cladding waste is to be neutralized to pH 10 before transfer to waste storage tanks. This treatment causes the precipitation of zirconium oxide or hydroxide, which may lead to flow difficulties during transfer. The purpose of this investigation was to determine the physical properties and flow characteristics of the neutralized slurry to assist in the selectin of satisfactory transfer equipment and storage conditions.

An investigation of the lateral stability and control effectiveness of a 0.0858-scale model of the Lockheed XF-104 airplane has been conducted in the Langley 16-foot transonic tunnel. The model has a low aspect ratio, 3.4-percent-thick wing with negative dihedral. The horizontal tail is located on top of the vertical tail. The investigation was made through a Mach number range of 0.80 to 1.06 at sideslip angles of -5 deg. to 5 deg. and angles of attack from 0 deg. to 16 deg. The control effectiveness of the aileron, rudder, and yaw damper were determined through the Mach number and angle-of-attack range. The results of the investigation indicated that the directional stability derivative was stable and that positive effective dihedral existed throughout the lift-coefficient range and Mach number range tested. The total aileron effectiveness, which in general produced favorable yaw with rolling moment, remained fairly constant for lift coefficients up to about 0.8 for the Mach number range tested. Yawing-moment effectiveness of the rudder changed little through the Mach number range. However, the yaw damper effectiveness decreased about 30 percent at the intermediate test Mach numbers.

Discussing a uranium reconnaissance program undertaken to evaluate formations that were producing uranium and vanadium ore in the Sanastee area.

The in-plie slurry loop work is now being considered as a joint program between the PAR project and ORNL. It is proposed that PAR design, fabricate and test the in-pile loops and that ORNL operate the loops in-pile, dismantle the loops after irradiation and made the appropriate measurements to determine the radiation effects. This report gives the objects of the slurry in-pile program and outlines the facilities and operations required to execute ORNL's part of this program.

Due to laboratory interest in devices capable of production of high current with short rise times in gaseous discharges (plasmas), an experimental machine has been built and tested to obtain data applicable to the design of a high gradient magnetic induction machine. This machine consists of a condenser type energy storage bank air core coupled to a toroid in which the plasma is produced. It has been used to determine circuit parameters and the effect of these parameters on the plasma.

As previously reported, zirconium undergoes large dimensional increases after scaling in air in a critical temperature range, 700 degree-1050 degree C. This finding was observed with specimens of a constant thickness (0;062 in.) To study the thickness effect, a number of specimens ranging in thickness from 0.020 to 0.200 in. were scaled in air at a temperature (900 degree C) where the growth is a maximum for a given time. Both cold rolled iodine sheet and forged iodide bar stock were used. to determine the effect of orientation, specimens from the forged bar were obtained such that the scaling surface was either parallel to or perpendicular to the long axis of the bar.

Report presenting an investigation to determine the performance of a conical-nose supersonic diffuser at angle of attack. The inlet had a pivoting cone which could be oriented to any of several angles independent of the angle of attack of the diffuser. Results regarding total-pressure recovery and mass-flow characteristics, cowl lip position, cone position relative to angle of attack, shadowgraphs, and contour maps are provided.

From Summary: "An empirically derived basis for predicting the area, rate, and distribution of water-drop impingement on airfoils of arbitrary section is presented. The concepts involved represent an initial step toward the development of a calculation technique which is generally applicable to the design of thermal ice-prevention equipment for airplane wing and tail surfaces. It is shown that sufficiently accurate estimates, for the purpose of heated-wing design, can be obtained by a few numerical computations once the velocity distribution over the airfoil has been determined. The calculation technique presented is based on results of extensive water-drop trajectory computations for five airfoil cases which consisted of 15-percent-thick airfoils encompassing a moderate lift-coefficient range."

Memorandum presenting an investigation conducted in the 20-foot free-spinning tunnel with a scale model to determine the spin and recovery characteristics of the McDonnell XF3H-1 airplane. The effects of control settings and movements on the erect and inverted spin and recovery characteristics of the model were determined. Results regarding design gross weight loading, variation of loading, spin-recovery parachutes, pilot escape, landing condition, control forces, and recommended recovery technique are provided.

Report presenting an adhesive, FPL-710, which produces higher strength at temperatures up to 600 degrees Fahrenheit than previously obtained and possesses good resistance to aging at high temperatures. It also has acceptable resistance to creep and immersion in various organic solvents. Results regarding its strength properties, heating and aging resistances, and variables affecting bond strength are provided.

Report presenting an experimental investigation utilizing rocket propelled vehicles in free flight to determine some effects of fuselage interference, wing interference, and sweepback on the damping-in-roll characteristics of untapered wings with an aspect ratio of 3.7 and NACA 65A009 airfoil sections between a range of Mach numbers.

Report presenting an investigation of the altitude operational characteristics of a prototype model of the J47D turbojet engines, which includes an afterburner, a variable-area exhaust nozzle, and an integrated electronic control in an altitude wind tunnel. Results regarding compressor stall, compressor unstall, combustor blow-out during acceleration, stall and blow-out protection, acceleration characteristics, deceleration characteristics, and altitude starting characteristics, afterburner operational characteristics are provided.

Well-type scintillation counters have found use in many radiochemical laboratories. A gamma scintillation well counter has been used to measure the gamma activity of liquid samples in the 325 Building counting room for about a year. This well counter has been built and calibrated so that gamma activity measurements made with it can be easily compared with measurements made with the gamma scintillation counter (GSC). The well counter is electronically identical to the present GSC and differs only in the shape of the crystal used and the physical arrangement of the lead shield. The crystal contains a well which allows a tube containing the sample to be inserted in the crystal. The physical arrangement of the detector greatly simplifies the preparation of liquid samples for activity measurement. The 325 Building well counter and its application to chemical research and plant process analysis will be discussed in the following paragraphs. An operating procedure is also included.

The rate of uranium sorption by a strong-base anion-exchange resin (Dovex 21K) from a uranyl sulfate solution (U 0.005 M, H2SO4 0.02M, SO4 0.2 M) was studied using a stirred vessel technique and measuring the U235 gamma radiation on each bead. Resin initially in the chloride form and the sulfate for was studied.

Progress report of the Brookhaven National Laboratory Nuclear Engineering Department providing updates on various projects, experiments, and other work. This report includes a summary of scholarly output from the reactor physics division, the applied chemistry and chemical engineering division, and metallurgy division.

Report presents results of tests made on a power control system by means of a ground simulator to determine the effects of various combinations of valve friction and stick friction on the ability of the pilot to control the system. Various friction conditions were simulated with a rigid control system, a flexible system, and a rigid system having some backlash. For the tests, the period and damping of the simulated airplane were held constant.

Uranium extractions from carbonate solutions were effective and phase separation rates were rapid using a new commercial quaternary extractant, Alamine 336. Extraction coefficients were approximately proportional to the quaternary concentration. Addition of -0.5 mole tridecanol/mole quaternary to the solvent gave optimum extraction efficiency and phase separation rates.

The following document is a note describing the building process of an improved nuclear density gauge in comparison to previous gauges, within the interval of June 1 to July 1, 1959.

This report discusses the concept of an improved mass gauging technique with a scintillation counter as the radiation detector in order to meet industrial requirements.