Report issued by the APDA over studies conducted on the Sodium Technology Loop. Methods, equipment, and results of the studies are presented and discussed. This report includes tables, illustrations, and photographs.

Reciprocal labelling in double-labelling experiments with H3- and C14- thymidine showed that when H3- thymidine (1μc/ml for 0.5 hr) was given first in the labelling sequence followed by a 4 hr interval before the C14- thymidine treatment, that passage of cells into and out of DNA synthesis was normal. When C14 was first in the sequence, the rate at which cells entered DNA synthesis was decreased. This was attributed to a radiation effect produced by the β-rays from the C14. The rate at which cells entered DNA synthesis was studied after 0.1, 1 and 10 rads of x-rays. A dose of 1 and 10 rads decidedly depressed the rate. Treatment of roots with 2, 20, and 200 μc/ml of tritiated water for 0.5 hr showed that the 2 higher concentrations produced an effect similar to the x-rays. This indicated that somewhere between 1 and 8 disintegrations per cell per 0.5 hr will produce a decrease in the rate at which cells enter DNA synthesis. In both the x-ray and H32O experiments the depression of the rate that cells entered DNA synthesis seemed to reach saturation at the higher doses.

From Introduction: "These first three chapters from a background of introduction and general ideas about dislocations. The next two chapters are concerned specifically with properties of ceramic materials, with emphasis on single crystals."

An accurate determination of the parameters of the resonance excited by the interaction of the 132 eV neutrons with the Co 59 target nucleus has been made, using the fast choppers at Brookhaven National Laboratory in the United States and Chalk River Laboratory in Canada. Neutron transmission through thick and thin samples resulted in the following parameters: [parameters not transcribed]. In addition, measurements of the resonance capture γ-ray intensity gave the value for the radiation width Γγ= 0.40 ± 0.04 eV, based on the known thermal capture cross section of cobalt of 37.5 barns. The reduced and total resonance capture integrals are calculated from the above parameters to be 50.5 ± 5.5 and 67.0 ± 5.5 barns, respectively. The above results are compared with previously determined resonance parameters and also with direct measurements of the total resonance capture integral.

The probabilities for nine electronic transitions among the low lying excited states in the C2 molecule are calculated by the dipole moment operator method and are given in the form of oscillator strength (or f values).

Liquid Metal Fuel Reactor Experiment program annual technical report.

Annual report of the Liquid Metal Fuel Reactor Experiment describing progress during calendar year 1958 and as well as an evaluation of progress and plans for future work.

Memorandum presenting the results of wind-tunnel oscillation tests to measure the rotary derivatives of a research airplane configuration at supersonic speeds. Measurements were made of the damping in yaw, pitch, and roll, the static longitudinal and directional stability derivatives, the effective-dihedral derivative, the rolling moment due to yawing, and the yawing moment due to rolling. The configuration was found to be statistically stable throughout the Mach number range, although its stability was becoming marginal at high angles of attack at Mach number 3.5.

Several compatibility test of various materials in contact in sodium under 500 psi pressure were conducted for 716 hr at 1500 F. Of the diffusion couples studies, the Inconel-beryllium system showed the largest amount al alloying. The reaction between molybdenum and beryllium resulted in the formation of two compounds, both of which were severely cracked in several areas. The molybdenum-INOR #8, and the INOR #8p type 316 stainless steel interfaces showed little if any alloying.

From Introduction: "The purpose of this paper is to present an analysis of the data for the remaining airplanes where the data were sufficient to warrant analysis. The data analyzed represent totals of 351 to 5660 hours of operations with ten types of Navy airplanes and were recorded during the period 1949 to 1953."

Report presenting testing of a towed airplane model in the 19-foot pressure tunnel in conjunction with the development of a flutter testing technique. The model was equipped with an autopilot to keep the model flying straight and level in the tunnel while restrained only in drag. Results regarding period and cycles to damp to half amplitude, time histories, and motions of the flexible wing model are provided.

From introduction: "The objective of this report is to present the results and describe the tests of both the 2-in. D and 6-in. D contractors using mill pulp feeds. Work on determining resign attrition is also reported. ORNL-CF-52-12-101 described the results of preliminary tests using synthetic ore pulps."

Report presenting the results of a wind-tunnel investigation to determine the effects of various free-flight rocket-model booster-adapter configurations on the aerodynamic characteristics in pitch and sideslip of a swept-wing, fighter airplane model with a Mach number of 2.01. Results regarding the effect of adapter shape and aerodynamic characteristics of the model alone are provided.

Report presenting results of a wind-tunnel investigation to determine the effects of various free-flight rocket-model booster-adapter configurations on the aerodynamic characteristics in pitch and sideslip of a swept-wing, fighter airplane model for a Mach number of 2.01. Normal-force, lateral-force, pitching-moment, and yawing-moment coefficients of the airplane model were measured, and schileren photographs of the various configurations were obtained.

From Summary: "Measurements of pressure distributions have been made over a wing midsemispan station on the 35 degree sweptback wing of the Douglas D-558-II research airplane at Mach numbers from 1.17 to 2.0. The results of the investigation indicate that, as the angle of attack increased at the higher Mach numbers, the pressure coefficient for a vacuum limited the extent to which the upper-surface pressures could expand. Consequently most of the increase in section normal-force coefficient at high angles of attack can be attributed to the increase in pressure over the lower surface."

Preliminary results are presented from an investigation to determine the influence of afterbody geometry on the effects of a sonic propulsive jet at transonic speeds. The results presented are base pressure coefficient and afterbody pressure-drag coefficient as a function of jet pressure ratio for different values of Mach number and jet temperature. Geometric parameters investigated include boattail angle, jet-to-model diameter ratio, and jet-to-base diameter ratio.

Abstract: "The trajectory analysis of an immobilized plasma has been generalized to include the presence of electrons having a far similar radius of gyration and, therefore, fitting readily into the broader scale structure established by the ions. This problem has been adapted to machine calculations and the results for various strengths plasmas have been calculated."

Report presenting the effects of nacelle location on the zero-lift drag of 45 degree sweptback wing-body combinations with boattail and cylindrical afterbodies at a range of Mach and Reynolds numbers. The nacelles were located at three different areas and the afterbody shape was also altered by replacing the boattail afterbody with a cylinder. Results regarding faired curves of the variations of total drag, base drag, and fin drag coefficients, and applicability of the transonic area rule are provided.

Report presenting the effect on base pressure of bleeding air to the semidead-air region at the trailing edge of two-dimensional blunt-trailing-edge airfoils at two Mach numbers. Variation of base pressure with base-bleed rate was determined for two airfoils profiles with both laminar and turbulent boundary layers approaching the trailing edge. Results regarding the effects of jet geometry, effects of jet area, effect of base bleed on the flow in the wake, effect of angle of attack, effect of Reynolds number, correlation of the results with mass-flow rate of the bleed air, and effect of base bleed on the drag of blunt-trailing-edge airfoils are provided.

Report presenting a flight investigation of a rocket-launched ram-jet engine incorporating an end-burning solid fuel. Results regarding acceleration, altitude, booster separation, survival time of booster adapter, and air specific impulse are provided.

Abstract: Preliminary reconnaissance for uranium in the Green River Basin and the Rock Springs Uplift revealed anomalous radioactivity northwest of Oregon Buttes in the Tipton tongue of the Green River formation and in the Cathedral Bluffs tongue of the Wasatch formation, and in the Tipton tongue in Red Creek Basin.

Report presenting an investigation in the transonic blowdown tunnel between Mach numbers of 0.65 and 1.4 to determine whether the principles of the transonic area rule could be used to improve the transonic drag-rise characteristics of a semielliptical shaped sweptback air inlet installed in the root of a sweptback wing-body combination. Results regarding the effect of the inlet and the interaction of Mach number and drag coefficient are provided.

Introduction: "The problem of determining the properties and necessary controls on the TBP Plant waste disposal to eliminate transport line plugging and to permit higher concentration prior to return of this to the tank farms was studied. A report of preliminary findings was made to L. W. Finsh on January 31, 1953. This report compiles information in the aforementioned report and findings since its issuance. Previous studies related to this problem are summarized in the U. R. Technical Manual, HW-19140."

Report presenting an investigation of spoilers at a Mach number of 1.93 to determine the effects of height and chordwise location on the section pressure distributions and section aerodynamic characteristics of a two-dimensional, 6-percent-thick, symmetrical wing. Spoilers of 3-, 5-, and 7-percent-chord height were tested at three chordwise locations. Results regarding pressure distributions, aerodynamic characteristics, and shock boundary-layer interactions are provided.