Modifications to the 100-K water plant will be made, under Project CG-775, to increase total process water flow rates to 175,000 gpm or greater. Included in the modifications will be the installation of new pump impellers for the primary and secondary process water pumps located in the 190-K Buildings.

This is a listing of the classified periodic and series reports originated at the Hanford Atomic Products Operation for the period 1943 to June, 1953, and of similar reports received from the Hanford Operations Office. This listing also traces the continuity of reports that have undergone title changes during this period. This has been done by cross referencing to titles previously or subsequently used. The primary grouping of these reports is according to the intervals at which they were issued, e.g., weekly, monthly, annually, etc. Within each group, the reports are arranged alphabetically by title; for each individual title a note at the right hand margin gives the inclusive dates for the period during which reports of that title were issued. Those not shown with closing date are being issued currently. Specific document numbers for each title are found in the catalogs of the 700 Area and 300 Area Classified Files. The list is intended primarily to assist Classified Files in locating periodic reports requested by Plant personnel. However, it is also hoped that it may emphasize to authors the need for retaining an established title for a periodic report. Unnecessary changes of title every few months for the same …

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Report for the Imperial Sugar Company describing the estimated daily cash balances for the company.

"Flutter models of the upper and lower vertical tails of an air-to-ground missile have been tested in the Mach number range from 0.5 to 3.0. It was found that the upper surface exhibited more or less conventional flutter behavior throughout the Mach number range, whereas the lower surface experienced a sudden change in flutter mode at a Mach number of about 1.18. This change in flutter mode was accompanied by a decrease of about 50 percent in the density required for flutter to occur" (p. 1).

Report presenting an investigation of an NACA submerged inlet operating over a range of mass-flow ratios and oncoming flow angles through a range of Mach numbers by use of a transonic bump. Results regarding the ram-recovery ratio, pressure distributions, and tuft studies are provided.

Report presenting load measurements using the swept-wing Bell X-5 and Douglas D-558-II research airplanes during flights in which reductions of longitudinal stability were experienced when pilots attempted to perform routine test maneuvers at moderate values of lift. Results regarding the maximum angles of attack and sideslip measured, pitching accelerations, horizontal-tail loads, wing loads, and stability deficiencies are provided.

Report presenting an investigation in the full-scale tunnel to determine the effects of a Fowler type slotted flap on the aerodynamic characteristics of a semispan 49.1 degree sweptback wing with NACA 65A006 airfoil sections streamwise, an aspect ratio of 3.78, and a taper ratio of 0.59. Results regarding the pitching-moment curve, effect of flap deflection, and lift increments are provided.

Report presenting an investigation to evaluate the effects of nacelles and extended split flaps on the longitudinal characteristics of a wing-fuselage-tail combination of a type believed to be suitable for long-range high-speed airplanes. Wind tunnel tests to study the effects of the nacelles and flaps were conducted at a range of Mach and Reynolds numbers. Results regarding the effects of the nacelles with the tail off, effects of tail height, effects of nacelles with the tail on, and effects of flaps are provided.

From Introduction: "The airfoil sections tested, which differ only in thickness ratio, were the NACA 64-006, 64-008, 64-010, and 641-012. Lift, drag, and pitching-moment data were obtained for Mach numbers of 0.3 to that for tunnel choke at angles of attack of -2^o to 31^o. The results of this investigation are reported herein."

Report presenting an investigation to determine the effects of center-of-gravity position on the gust loads of a delta-wing model with the leading edge swept back 60 degrees. A 15-percent change in the center-of-gravity position on the mean geometric chord produced a 7.5-percent change in load for the model in a sharp-edge gust and a 35-percent change in load in a gust with a 6.5 chord gradient distance.

An investigation was made to determine the effects of vertical-tail size and length and of fuselage shape and length on the static lateral stability characteristics of a model with wing and vertical tails having the quarter-chord lines swept back 45 degrees. The results indicate that the directional instability of the various isolated fuselages was about two-thirds as large as that predicted by classical theory.

"An experimental and analytical study has been made of some features of the turbulent heat diffusion behind a line heated wire stretched perpendicular to a flowing isotropic turbulence. The mean temperature distributions have been measured with systematic variations in wind speed, size of turbulence-producing grid, and downstream location of heat source. The nature of the temperature fluctuation field has been studied" (p. 1).

Memorandum presenting rudder-pulse maneuvers performed with a swept-wing fighter-type airplane at altitudes from 30,000 to 43,000 feet over a Mach number range of 0.71 to 1.48 to determine the lateral stability characteristics relative to the stability axes, in general, and the lateral derivative characteristics, in particular. Four configurations were employed; three involves different vertical tails with varying aspect ratio or area and the fourth employed a large tail with an extension of the wing tips.

Introduction:"A corrosion test program in support of the Redox Project was carried out during the second quarter of 1950 to determine the corrosion rates of several austenitic stainless steels in simulated 202-B Waste Storage solution containing HF, HN03, and H2SO4 acids. The results of this program are contained herein and all original data are recorded in laboratory notebook HW-3282-T."

A kinetic study of the accumulation of C{sup 14} in the intermediates of steady state photosynthesis in C{sup 14}O{sub 2} provides information regarding the sequence of reactions involved. The work described applied the radio-chromatographic technique for analysis of the labeled early products. The simultaneous carboxylation reaction resulting in malic acid as well as phosphoglycerate is demonstrated in experiments at high light intensity. A comparison of radioactivities in a number of phosphorylated sugars as a function of time reveals concurrent synthesis of fructose and sedoheptulose phosphates followed by that of ribulose phosphates and later by that of glucose phosphates. The possibility that the cleavage of C{sub 4} compounds to C{sub 2} carbon dioxide acceptors may involve C{sub 7} and C{sub 5} sugars and evidence for this mechanism is presented.

Report discussing thermodynamic measurements and calculations made regarding couples of neptunium ions in perchloric acid.

The nuclear characteristics and fuel costs of a number of aqueous homogeneous reactors have been estimated. Most of the reactors studied were cylindrical, two-region power-breeders variously having between 0 and 300 g/l of thorium in the core and between 500 and 1000 g/l of thorium in the blanket. The results of the calculations, including breeding ration, fuel inventories, doubling times, and net fuel costs, are summarized in this report.

A self-contained developmental or the formation of the problem of inelastic neutron scattering by crystals is presented. although nearly all of the methods and results used in the present discussion have appeared in a variety of previously published papers, additional mathematical details are given here which have been found by thee authors to aid in understanding the final results.

Information on experimental facilities and reactors.

Report describing the Hanford Atomic Works' Plutonium Recycle Test Reactor, its siting concerns, operation, and safety concerns.

Memorandum presenting an investigation of the flow characteristics over a 6-percent-thick symmetrical circular-arc airfoil section with a 30-percent-chord trailing-edge flap at a Mach number of 6.90 and a Reynolds number of 1.65 x 10(sub 6). The model was tested over an angle-of-attack range of 0 to 16 degrees and a flap-deflection range of -16 degrees to 16 degrees. Results regarding pressure results and aerodynamic characteristics are provided.

Report presenting testing of a 4.5 inch by 4.5 inch tunnel with slots in two opposite walls in order to determine the effects of various slot exit shapes, mixing sections, and diffusers on power requirements. Some of the data obtained included measurements of the pressure ratio required to operate the tunnel, the effects of auxiliary bleed flow, diffuser static-pressure ratios and distributions, and diffuser total pressure distributions.

Report presenting the results from 20 hours of service operational flying of an instrumented North American F-100A fighter airplane. Results regarding the altitude and Mach number, normal-load factor, airplane attitude, use of controls, rolling motions, pitching motions, yawing motions, vertical-tail loads, horizontal-tail loads, and a comparison with other airplanes are provided.