This report covers the laboratory and pilot plant investigation of the reclamation of the low hafnium zirconium fines resulting from the manufacture of zirconium sponge and zirconium crystal bar. The process investigated involved recovery of the zirconium as zirconium tetrachloride, by drying the fines in an atmosphere of nitrogen and subsequent chlorination of the fines with anhydrous hydrogen chloride at temperatures above the sublimation point of the product.

Introduction: A proposal for using an energetic neutral deuteron beam for injection into a mirror machine has been made by Eugene Lauer. This report describes an experimental attempt to produce a large neutral deuteron beam. The beam from the NTA ion source was passed through a target of hydrogen gas where the charge exchange mechanics produced a beam of energetic neutral deuterium atoms.

"An analysis is presented of the accidental release of activity following the operation of the NS "Savannah" at the New York Shipbuilding Corporation docks in Camden, New Jersey. Although a number of accidents are considered, the report is primarily concerned with the environmental activity levels and subsequent exposures which would result from the "maximum credible accident" (p. v).

Introduction: This report describes the Integral Neutron Thermalization activities at General Atomic from October 1, 1962, through September 30, 1963.

Report presenting an investigation of the flutter characteristics of a series of thin cantilever wings with taper ratios of 0.6 for a range of Mach numbers. Results regarding flutter frequencies, time histories, effects of sweep on the flutter-speed ratio, effects of aspect ratio on the flutter-speed ratio, effects of additional models on the reference flutter speed, application of the flutter-speed ratio, and modified experimental flutter-speed coefficient are provided.

Local heat-transfer coefficients, temperature recovery factors, and pressure distributions were measured on the front side of a circular cylinder at a nominal Mach number of 3.9 over a range of free-stream Reynolds numbers from 2.1 x 10 to the 3rd power to 6.7 x 10 to the 3rd power and yaw angles from zero degrees to 44 degrees. Yawing the cylinder reduced the heat-transfer coefficients and the pressure drag coefficients. The amount of reduction may be predicted by a theory presented herein.

Memorandum presenting a transonic flutter investigation of models of the all-movable horizontal tail of a fighter airplane in the transonic blowdown tunnel. The models were dynamically and elastically scaled by criteria which provide a flutter safety margin. Results regarding some general comments, simulated airplane tests, effects of pitch stiffness with rearward pitch axis, and effect of pitch-axis location are provided.

Report presenting an investigation of the low-speed static longitudinal and lateral stability characteristics of a model with an M-wing in mid and high positions and with three horizontal-tail heights. The wing had its sweep discontinuity at 40-percent wing semispan, an aspect ratio of 6, a taper ratio of 0.60, NACA 65A009 airfoil sections parallel to the plane of symmetry, and 45 degrees sweep of the quarter-chord lines. Results regarding longitudinal stability characteristics and lateral stability characteristics are provided.

A cermet composition was investigated as a potential material for gas-turbine blades. Blades of HS-21 alloy were also operated in the engine simultaneously to provide a basis of comparison. The cermet blades survived as long as approximately 312-1/2 hours at about 1500 degrees F with an average midspan centrifugal stress of approximately 11,500 psi.

"An NACA 65(sub 1)-212 airfoil of 8-foot chord was provided with a gas-heated leading edge for investigations of cyclical de-icing. De-icing was accomplished with intermittent heating of airfoil segments that supplied hot gas to chordwise passages in a double-skin construction. Ice removal was facilitated by a spanwise leading-edge parting strip which was continuously heated from the gas-supply duct. Preliminary results demonstrate that satisfactory cyclical ice removal occurs with ratios of cycle time to heat-on period (cycle ratio) from 10 to 26" (p. 1).

Memorandum presenting an analysis of the effect of adding fluorine to the Vanguard first-stage oxidant. An increase in specific impulse of 5.74 percent may be obtained with 30 percent fluorine. Charts are provided regarding the vehicle performance increases for a zero-drag vertical trajectory.

The first report in a series of five that present unanalyzed pressure data obtained in tests of five full-scale propellers with NACA 16-series blade sections. Pressure distributions on the blade sections were measured under operating conditions to determine the aerodynamic characteristics of each blade section. This particular report presents information for eleven radial stations of the NACA 10-(3)(066)-033 propeller.

Report presenting a study of the effect of sweep on wings with the NACA 65A006 airfoil section in the 8-foot high-speed tunnel. This particular investigation included a wing with that airfoil section, 60 degrees of sweepback at the quarter chord, an aspect ratio of 4, and a taper ratio of 0.6. Results regarding force and moment characteristics and wake and downwash characteristics are provided.

Report presenting an investigation in the supersonic blowdown tunnel of spoilers on two unswept wing arrangements at Mach numbers of 1.90 and 1.96. The effect of pressure-distribution tests on an unswept airfoil in the presence of a fuselage but without tip effects indicated that spoilers could be oppositely deflected in a manner similar to flap-type ailerons to obtain roll effectiveness without loss in lift. Results regarding force and moment tests are also provided.

Report presenting pressure-distribution measurements on two large-scale semispan wing-fuselage models with 45 degrees of sweepback, an aspect ratio of 6, a taper ratio of 0.5, and 10-percent-thick sections normal to the quarter-chord line. Adding camber and twist to a wing significantly improved the upper surface loading of the wing at a lift coefficient of 0.4 through a reduction in the peak negative pressure coefficient. Results regarding loading characteristics and stalling characteristics are provided.

Report presenting a free-flight investigation to determine some effects of aileron span and deflection on the rolling effectiveness of plain, sealed, 15-percent- and 30-percent-chord flap-type ailerons through a range of Mach numbers. Wings of different degrees of torsional flexibility were tested and the results were extended to estimate rigid-wing rolling-effectiveness of all aileron configurations tested.

From Introduction: "This report presents calculations of the angularity of the air stream with respect to the vertical tail for a rolling airplane, the interference effects of the wing being taken into account. A discussion of the factors which enter into the calculations is given and equations for applying the side-wash results to the determination of the tail contributions to the rolling-stability derivatives are included. The results are compared with some available experimental data."

Memorandum presenting an investigation with a ramjet utilizing pentaborane fuel in order to evaluate promising high-energy fuels under actual flight conditions. During descent, the engine accelerated to a Mach number of 1.45 when a flame-out believed due to spray-bar failure took place. Results regarding time history, pressure recovery, thrust, thrust-minus-drag, and drag coefficient, and comparison with hydrocarbon fuel are provided.

The following report describes the Astron Thermonuclear Program initiated at Livermore, California in 1957.

This report is the result of a study to develop heat-resistant fin materials possessing a high thermal conductivity for air radiators. Since an economical and commercially feasible product was desired, the investigation was restricted primarily to a study of electroplated copper, clad copper, and copper alloys. Sheet material 0.008 to 0.010 in. thick was evaluated for fabricability and for metallurgical stability and thermal conductivity at 1500°F. From the results of the rests it was concluded that: (1) electroplates were unsatisfactory; (2) clad-copper fins possessing a thermal conductivity of 50% of that of copper are commercially feasible; (3) copper-aluminum alloys possessing a thermal conductivity approaching that of copper at 1500°F are possible. Service tests of clad copper and the copper-aluminum alloys indicate that the choice of materials will be dictated by the requirements of the radiator, since each presents some unique problems.

Report that "is a supplement to IDO-16332, "The Engineering Test Reactor Critical Facility Hazards Summary Report", presenting information on the conduct in the Facility of certain experiments which are expected to be operated in the Engineering Test Reactor" (p. 3).

Increasing the volume and length of the duct behind the inlet affected the inlet stability at Mach 2.0 and zero angle of attack. Close approximation of the inlet stability limit of the J34 engine-inlet configuration was obtained by a cold-pipe configuration having a length and volume approaching that measured to the engine turbine. Variation of these parameters had a small effect on the minimum subcritical stable mass flow below a cowl-lip-position parameter of 44 degrees and appeared to have a negligible effect on the inlet pressure-recovery - mass-flow curve. Initial buzz frequency and minimum cowl-lip-position parameter for complete buzz-free operation varied with configuration.

Report presenting an investigation of the transonic flutter characteristics of models of an all-movable horizontal tail of a fighter airplane. Results regarding simulated airplane tests, the effects of pitch stiffness with rearward pitch axis, and the effect of pitch-axis location are provided.

Report presenting a wind-tunnel investigation to determine the effectiveness of area suction in increasing the lift of a moderately thick straight wing encountering trailing-edge air flow separation. Results regarding a model with undeflected leading-edge flap and tip tanks on and a model with the tip tanks removed are provided.