Abstract: "Decontamination factors of the order of 10-4 were obtained for Beta and Gamma emitters present as fission products when uranium was precipitated from 50 mC activity level solutions as uranyl oxalate under normal uranium yield conditions for three cycles (~60%). Factors of the order of 10-3 were obtained by the use of this reaction with similar solutions under relatively high uranium yield conditions for three cycles (~90%). The uranium peroxide precipitation reaction proved to be of no value on such solutions, yielding decontamination factors of only 17.1 Beta emitters and 1.2 for Gamma emitters for three cycles."

Technical report describing a rapid and quantitative radiochemical method for the analysis of neptunium (237). This method is based on the extraction of neptunium (IV) with thenoyl-trifluoracetone in xylene. Neptunium (237) is separated free from other alpha emitters and from non-radioactive interferences, and the method may be readily adapted to remote control. [From Abstract]

Memorandum presenting an investigation of aileron effectiveness and dihedral effect for a wing-body combination with a variable-incidence triangular wing with modified half-delta controls at the wing tips. The tests were conducted at a Mach number of 1.52 at a Reynolds number of 0.82 million. The experimental value of aileron effectiveness at 0 degrees angle of attack was approximately 78 percent of the value predicted by linear theory, and the effectiveness decreased with increasing wing angle of attack.

Report presenting a preliminary investigation in a duct system with fully developed pipe flow to determine the effectiveness of vortex generators in improving the performance of a 21-inch-diameter straight-outer-wall annual diffuser with an overall equivalent conical expansion angle of 15 degrees and a and 1.9:1 area ratio. The vortex generators used were rectangular noncambered airfoils that varied in chord, span, angle of attack, number, and location. Results regarding a diffuser with no vortex generators, a diffuser with vortex generators on inner body, and a comparison of the diffuser performance with and without vortex generators are provided.

Report presenting flight testing of a missile model with cruciform, triangular, interdigitated wings and tails to determine the longitudinal stability and control characteristics over a range of Mach numbers. Results regarding static stability and damping, control effectiveness, and control hinge moments are provided.

Over-all performance of a two-stage turbine from a J35-A-23 turbojet engine is presented. Limiting blade loading restricted work output to approximately 95 percent of the design value. The brake internal efficiency at design operating conditions was approximately 0.75. maximum brake internal efficiency at off-design conditions was between 0.81 and 0.82.

Report presenting a theoretical investigation of an automatic control system with primary sensitivity to normal accelerations as used to control a specific supersonic canard missile. The control system is made up of an integrating servomotor that receives a signal from an accelerometer that is sensitive to normal accelerations of the airframe that it is controlling. The acceleration control system appears to work well for obtaining longitudinal control, but works best when combined with a homing seeker or guidance system for controlling directional space.

Report presenting an investigation to determine the effects of partial-span single slotted and double slotted flaps at various deflections on the longitudinal aerodynamic characteristics of a sweptback-wing-fuselage combination. Results regarding the lift characteristics, pitching-moment characteristics, drag characteristics, and effect of flap-bracket alignment are provided.

From Summary: "This paper supplements a previously published one on the effect of design parameters on ditching characteristics. The supplementary information is based on additional data available from both model tests and full-scale experience. In addition, summary tables compiled from the NACA model ditching investigations are presented."

An investigation was conducted on an axial-flow-compressor type turbojet engine in the NACA Lewis altitude wind tunnel to determine the operational characteristics of several ignition systems, cross-fire tube configurations and fuel systems over a range of simulated flight conditions. The opposite-polarity-type spark plug provided the most satisfactory ignition. Increasing the cross-fire-tube diameter improved intercombustor flame propagation. At high windmilling speeds, accelerations to approximately 6200 rpm could be made at a preset constant throttle position. The use of a variable-area nozzle reduced acceleration time.

Report presenting rocket-powered flight testing to determine the damping in roll of several wings of 0 degree and 45 degree quarter-chord-line sweep with various taper ratios for a range of Mach numbers. Damping in roll decreased with decreasing taper ratio at roughly the same rate for swept and unswept wings and also decreased by sweeping the quarter-chord line. The experimental results were also consistently lower than what was predicted by theory.

Report presenting an aerodynamic investigation in the high-speed 7- by 10-foot tunnel to determine the effects of taper-in-thickness on the aerodynamic characteristics of wings with 35 and 45 degrees of sweepback, aspect ratio 6, and taper ratio 0.60. The wings were tested over a range of Mach numbers.

Report presenting an investigation to determine the aerodynamic characteristics of a series of thin, rectangular wings in the 16-foot high-speed wind tunnel using the transonic bump technique over a range of Mach and Reynolds numbers. Lift, drag, and pitching moment characteristics are presented for wings of 4 different aspect ratios and NACA 63A0XX sections and with 5 different thickness-to-chord ratios.

Theoretical performance for liquid lithium and liquid fluorine as a rocket propellant was calculated with assumptions both of equilibrium and frozen composition during expansion. Parameters included were specific impulse, combustion-chamber temperature, nozzle-exit temperature, composition, mean molecular weight, characteristic velocity, coefficient of thrust, and ratio of nozzle-exit area to throat area. For chamber pressure of 300 pounds per square inch absolute and expansion to 1 atmosphere, the maximum equilibrium specific impulse calculated was 335.5 pound-seconds per pound. The effect of ionization on calculated performance was shown to be negligible by comparison of values of various parameters calculated both with and without ionized products of combustion.

Report presenting a low-speed wind-tunnel investigation to determine the longitudinal aerodynamic characteristics of a 47.7 degree sweptback wing-fuselage combination with split flaps and several modifications. The lift characteristics, pitching-moment characteristics, drag characteristics, and a comparison with flaps of the slotted type are included.

"Aileron effectiveness and dihedral effect were investigated for a wing-body combination having a variable-incidence triangular wing with modified half-delta controls at the wing tips. The tests were conducted at a Mach number of 1.52 at a Reynolds number of 0.82 million. At the Mach number of the tests, the Mach cone from the wing apex was almost coincident with the wing leading edge" (p. 1).

Report presenting the effects of sweepback on the occurrence and principal characteristics of single-degree-of-freedom aileron flutter for a wing-aileron combination. Testing occurred over a range of Mach and Reynolds number and angles of attack. Results regarding the measurements of aileron motion, effect of sweep, variation of lift coefficient, and use of shadowgraph technique for visualizing flow are provided.

A numerical method was developed for calculating thermal stresses in irregular cylinders cooled by one or more internal passages. The use of relaxation methods and elementary methods of finite differences was found to give approximations to the correct values when compared with previously known solutions for concentric circular cylinders possessing symmetrical and asymmetrical temperature distributions.

The following report records a total of forty-nine graphite core samples that have been bored from process tube blocks in the Hanford piles with the intention to provide results to indicate that core boring is an entirely practical operation over bore scraping in obtaining powder samples.

The following document provides figures with all information that describe the heavy water moderated chain reacting pile at Argonne National Laboratory.

The following report records a total of forty-nine graphite core samples that have been bored from process tube blocks in the Hanford piles with the intention to provide results to indicate that core boring is an entirely practical operation over bore scraping in obtaining powder samples.

The total cross sections of the reactions DDp, DDn, TD at 10 kev to 10 Mev are estimated from a review of the experimental data up to January 1951. Maxwell averages for DDp and TD computed from these estimates are given, together with some fitted analytic expressions provided for machine use. A collection of the identifiable earlier estimates is also included for reference and for comparison with the new figures. For relative order of magnitude purposes, cross sections and the derived Maxwell averages are given down to 50 ev using the theoretical Gamow slopes for the extrapolation. Gamow plots for the derived cross sections above l0 kev arc also given. Much of the primary experimental data exists in the form of thick target yields and we find the most uncertain factor in converting these thick targets yields into cross sections is the magnitude of the D/sub 2/O stopping cross section. The particular D/sub 2/O stopping cross section relation used in this derivation together with some of the earlier stopping cross sections are given. Thick target yields are included for both DD and TD on D/sub 2/ targets, at 0.01 to 1 Mev, experimental values being supplemented by calculated values.

Uranium has been successfully impact extruded into typical cylindrical shapes of conventional design. Extrusion was carried out in the "gamma" region by heating cast uranium slugs to a temperature of approximately 1050 degrees C. Protection against oxidation was afforded by surrounding the slugs during heating with an inert atmosphere of argon gas. Impact extruded shapes possessed physical properties which are better than the properties of as-cast metal. Also, extruded shapes show a uniform internal structure with flow lines characteristic of commercial impact extruded pieces formed from other metals. Impact extrusion, as a fabricating processes for uranium, maybe applied successfully to produce complicated shapes or forms not practical by casting or where savings in metal and machining time is desired. The process would not appear to be commercial unless a large quantity of pieces was required.

Technical report outlining the reconstitution of the Homogeneous Reactor Experiment Project (HRE) as the Homogeneous Reactor Project. Report covers the need for a broader developmental program to establish the feasibility of obtaining the potential advantages of homogeneous reactors for the production of fissionable materials and power. Details the ultimate objective of the ORNL program to provide the technical information required to determine the feasibility of a full scale plutonium power producing homogeneous reactor. [From Summary]