The method is based on caustic precipitation and centrifugation (which removes the Cs and small amounts of Sr, rare earths, Zr, Nb, and Ru). These are removed in the supernatant and run through a cation exchange column. This separates Zr-NB and Ru. The effluent is precipitated and the Zr-Nb is stored in an asphalt pit. The Ru then may be recovered from the precipitate. The precipitate from the original centrifugation is calcined, pressed and transported to a deep well.

Report presenting an analysis to determine the effect of increasing the fin-chord length while holding the span constant on the lift and longitudinal static stability of fin-body combinations. Rectangular and triangular fins with spans of 2 and 3 body diameters in combination with a fineness-ratio-14 ogive-cylinder body were tested.

Report presenting an investigation to determine the effect of a Küchemann type fuselage modification designed to reduce the interference velocities at the wing-fuselage junctures on the longitudinal characteristics of a wing-fuselage-tail combination and several wing-fuselage combinations. The tests were made through an angle-of-attack range at Mach numbers varying from 0.60 to 0.92 at a Reynolds number of 2 million. Results regarding the 64A wing-fuselage-tail combination, four-digit wing-fuselage combinations, and effects of Mach number are provided.

The compressor case of a 13-stage axial-flow compressor was modified to incorporate air-bleed systems over the fifth and tenth rotor stages. Rotating stall-exited rotor-blade vibrations were measured in the first and second stages at 60 and 68 percent of rated speed, respectively. Either the fifth- or the tenth-stage bleeds satisfactorily eliminated the peak vibratory stresses.

Few data exist for the thermal conductivity and viscosity of gases at very high pressure. The possibility of using gases for heat transfer media at pressures up to 100 atmospheres and above raised the problem of estimating variations in the conductivity and viscosity at high pressure. Generalized plots are presented which are based on the work of Enskog, Eucken, and Hirschfelder et al. Some pertinent data from Hirschfelder et al and from Hilsenrath et al are presented.

Report presenting an analysis of horizontal-tail loads on a flexible multi-engined jet-propelled swept-wing medium bomber to determine the tail lift-curve slope due to tail angle of attack, tail-lift curve slope due to elevator deflection, tail pitching-moment coefficient due to elevator deflection, downwash factor, and elevator effectiveness factor. The effect of the stabilizer, effects of elevator flexibility, and effects of wing stability are presented.

The following temperature measurement tabulation consists of two parts. Part I lists all HRT thermocouples, their location, the junction box thru which the leads pass, and their termination, if on an instrument. Part II lists all temperature read out instruments and their location. A total of 577 thermocouples are listed in this tabulation. The roughly 77,000 ft of wire used in connecting them up cost $6,799. Temperatures are read on 24 instruments. Cost of these was approximately $15,688. Accessories such as patch panels, conduit, disconnects, etc., used in installing the thermocouples cost about $8,069. Total cost for material and instruments for temperature measure comes to approximately $30,556.

Performance of supersonic ramp-type side inlet with ram-scoop throat bleed and varying fuselage boundary layer removal at low supersonic speeds.

The horizontal and vertical power distribution for a 5 x 7 fuel element loading of the TSR is presented. (auth)

Plutonium sheet of uniform thickness and good surface can be made by the extrusion of a tube which is then split and flattened. This report describes the equipment and the operating conditions for making sheet 0.005 to 0.055 in. thick with areas up to 24 in. square.

Safety measures of the Livermore Pool Type Reactor in reaction to certain meteorological conditions and following the improbable rupture of the reactor building.

Report presenting a method for analyzing the effects of inertia and aerodynamic cross-coupling on the response of airplanes in rolling maneuvers. The method is based on the concept that variations in the calculated steady-state angle of attack and sideslip with roll rate give a measure of the onset and degree of roll coupling. An evaluation of this concept from several different perspectives is also provided.

From Introduction: "Experimental investigations of the combustion characteristics of diborane, pentaborane, and pentaborane-hydrocarbon blends in modified turbojet combustors have been conducted at this laboratory at the request of the Bureau of Aeronautics, Department of the Navy, as part of Project Zip. Results of these single-combustor tests are presented in references 2 to 5."

"Preliminary tests made by the General Electric Company indicated that aerodynamic loads might cause large enough distortions in the thin sheet-metal rings of a nuclear fuel element to result in structural failure. The magnitude of the distortions in a test fuel element was determined from strains measured with airflow conditions simulating those expected during engine operation. The measured vibratory strains were low enough to indicate the improbability of failure by fatigue. A conservative estimate of the radial deflection that accompanied peak strains in the outer ring was +0.0006 inch" (p. 1).

Memorandum presenting an investigation conducted in the 7- by 10-foot tunnel of the static longitudinal and lateral stability characteristics of a model with a 45 degree sweptback wing of aspect ratio 4 and with several different tail arrangements. The tail configurations studied had unswept, rectangular surfaces and included a T-tail and conventional fuselage-mounted horizontal and vertical tails. Results regarding wing-fuselage characteristics, effects of afterbody shape, effect of tail configuration on stability, and comparison of swept- and unswept-wing configurations are provided.

"ABS>Injection trajectories were calculated for different injection conditions for the Cambridge Electron Accelerator, considering also the effect of magnetic fringing fields. The general problem of matching the emittance of the linac to the acceptance of the synchrotron in the transversal phase space is considered, and it is shown that this can be done by a set of two quadrupole lenses. In order to eliminate rudial betatron oscillations due to energy deviations of the injected particles, a pulsed electric quadrupole lens in the synchrotron in combination with two deflectors between linac and synchrotron can be used to place particles of different energies on their specific equilibrium orbits. A layout of the whole injection system following the output of the linac is given."

Report presenting a five-degree-of-freedom analysis of aircraft maneuvering stability, which showed that gyroscopic moments due to engine rotor momentum produced considerable rolling asymmetry for certain values of stability derivatives and flight conditions. Results regarding the altitude effects, Mach number effects, initial load factor, effective dihedral, static stability, roll velocity, and comparison with simplified longitudinal- and lateral-mode theory are provided.

Memorandum presenting a preliminary and theoretical investigation of the effect of velocity diagram on inlet total-pressure distortions through single-stage subsonic axial-flow compressors for incompressible flow. A theoretical investigation was used to determine proper velocity diagrams and then the wake of a 1/4-inch-diameter rod was measured upstream of the rotor. The tests indicated that the derived equation will estimate the downstream distortion with reasonable accuracy for inlet total-pressure distortion which extends far enough circumferentially to alter the static-pressure field in the blade passage.

A plot of the pressure-drop data shows that the pressure drop through a single HRT off-gas adsorption unit is equal to 2.66 times the O2 flow (measured in liters/min at 70 F, 14.7 psia).

Report presenting an investigation to determine the internal-flow characteristics of three top-mounted scoop inlets with rounded lips. The inlets were mounted at the leading edge, midchord, or trailing edge of a high 45 degree sweptback 6-percent-thick wing. Results regarding the total pressures at inlet, flow distortions at inlet measuring station, and boundary-layer control are presented.

"An investigation has been completed in the Langley 20-foot free-spinning tunnel on a l/18-scale model of the Ryan X-13 airplane to determine its spin, recovery, and tumbling characteristics, and to determine the minimum altitude from which a belly landing could be made in case of power failure in hovering flight. Model spin tests were conducted with and without simulated engine rotation. Tests without simulated engine rotation indicated two types of spins: one, a slightly oscillatory flat spin; and the other, a violently oscillatory spin" (p. 1).

Report presenting testing of a modified 1/10-power nose shape in free flight at Mach numbers up to 6.7. Measured heating rates were presented and compared with calculated values. Results regarding transition and comparison with previous investigations are provided.

Memorandum presenting a discussion of oscillating flap-type and all-movable controls with particular emphasis on the aerodynamic forces and moments at transonic speeds. Hinge-moment results from recent wind-tunnel and rocket-powered-model tests are summarized for trailing-edge flap-type controls to illustrate the effects of control hinge-line position and profile shape on one-degree-of-freedom flutter of this type of control.

Report presenting an investigation of a five-stage rocket model at mach number 13.9 and an altitude of 81,500 feet. Temperatures were measured at 12 stations on the flat-face copper nose. Heating rates calculated from temperature time histories are compared to theoretical predictions of the rates.