From Introduction: "In the present investigation, lift, drag, and pitching moment were determined over a Mach number range 0.6 to 1.42. Smooth-water takeoff and landing stability and resistance were investigated. A brief check of the rough-water spray and behavior was also made."

Report presenting pressure-distribution data for a drooped-nose-fuselage forebody alone and with four canopy shapes mounted on the forebody. Two canopies had the same shape and size rearward of the windshield but one had a flat and one had a v-shaped windshield, and the other two canopies were located at different body sections with smaller maximum cross-sectional areas, higher fineness ratios, and flat windshields. Results regarding the effect of windshield shape, canopy location, Mach number, sideslip, and angle of attack are provided.

Report presenting measurements in a wind tunnel of the static and dynamic-rotary stability derivatives of a model with an unswept wing of low aspect ratio and a high horizontal tail. Tests were conducted at a range of Mach numbers and angles of attack. Results regarding a variety of aerodynamic characteristics are provided.

This report discusses the use of solvent extraction techniques at HAPO for separating plutonium from uranium and fission products which is rather expensive. This is in part due to solvent, chemical and process steam costs and in part to the need for complicated equipment to handle the process. It is felt that the use of ion exchange resin techniques might be economically attractive both as to lowered chemical costs and equipment simplification. Also, the decontamination achieved by solvent extraction is at time marginal. Changing to another process following partial decontamination by solvent offers the possibility of greater over-all DF`s.

The statistical approach to the gust-load problem, which consists in considering flight through turbulent air to be a stationary random process, is extended by including the effect of lateral variation of the instantaneous gust intensity on the aerodynamic forces. The forces obtained in this manner are used in dynamic analyses of rigid and flexible airplanes free to move vertically, in pitch, and in roll. The effect of the interaction of longitudinal, normal, and lateral gusts on the wind stresses is also considered.

There is a continuing high interest in the development of organic coolant technology for application to future Hanford reactors. In addition to the HAPO organic program, two other programs are being sponsored by the Atomic Energy Commission. These include the Naval Reactor program, aimed at a reactor for ship propulsion, and the Civilian Power Reactor program. Because of the similarity of the technical efforts in the three programs, an attempt is being made to establish effective liaison among the programs. To this end, a visit was made to several sites actively engaged in organic development work. These sites and their primary functions are detailed in this report.

Report presenting calculations by the method of characteristics of 2960 boundaries of supersonic axisymmetric free jets exhausting from conically divergent nozzles into still air. The calculations covered a range of jet Mach numbers, a ratio of specific heats of the jet, divergence angles of the nozzle, and jet static-pressure ratios. Results regarding the effect of increasing the static pressure ratio, the simulation of one jet boundary by another, and interpolation and extrapolation of calculated boundaries are provided.

This document presents a set of machine-computed curves involving a wide range of Kb and Kc, from which both thermal and resonance values of (E-1) may be obtained.

Ignition delays of a diallylaniline-triethylamine mixture and of triethyl trithioposphite with red fuming nitric acid were measured as a function of combustor dimensions, initial propellant temperature, and initial ambient pressure. Ignition delay increased with exhaust-nozzle diameter. Ignition delay also increased as propellant temperature decreased, but did not vary with initial ambient pressure except with the largest nozzle diameter. A correlation among ignition delay, combustor dimensions, and propellant temperature is presented, and the extension of the correlation to other systems is discussed.

Report presenting a wind tunnel investigation to determine the effects of a blowing type boundary-layer control flap on the longitudinal control and lateral stability and control of an F-86D airplane. Tests were made using the following lateral control devices: split-flap-type spoilers, differentially deflected flaps, and differential amounts of blowing over the flaps.

Report presenting an analysis of the blade-element performance of a highly loaded transonic rotor with double-circular-arc blades. The rotor was purposely loaded beyond the prudent level for exploratory purposes. Results regarding the radial-distribution plots, blade-element data, element blade-to-blade loss variation, and a comparison of steady-state and hot-wire measurements are provided.

Memorandum presenting a survey and evaluation of flutter research and flutter engineering, with particular emphasis placed on the design of primary fixed surfaces and primary controls. Analyses are made of recent flutter occurrences to delineate past and future problems, and detailed appraisals are given of the status of the various engineering branches involved in the analytical and experimental prediction of flutter.

The time-average characteristics of boundary layers over a flat plate in nearly quasi-steady flow are determined. The plate may be either insulated or isothermal. The time averages are found without specifying the plate velocity explicitly except that it is positive and has an average value.

This report presents a summary of certain physical properties that have been determined experimentally on the fluoride mixture that have been formulated at ORNL (Rers. 1, 2). These properties include the density, enthalpy, heat capacity, heat of fusion, thermal conductivity, viscosity, Prandtl number, electrical conductivity and surface tension. In addition to the experimental data, values have been predicted for the heat capacity and density of the other mixtures from the correlations of these properties. Estimates of the viscosity have also been made for a number of the mixtures on which no experimental data were available.

Progress report of the Oak Ridge National Laboratory Analytical Chemistry Division providing updates on various projects, experiments, and other work in ionic analyses, analytical instrumentation, radiochemical analyses, activation analyses, spectrochemical analyses, inorganic preparations, optical and electron microscopy.

The loading on the primary transformers which step down the 230 kv transmission voltage to a distribution voltage of 13.8 kv, at 100-B-C, 100-D-DR, 100-F, and 100-H Areas will be increased by the synchronous motors now being installed in those areas under Project CG-558. This report summarizes: The changes in electric loads (both kv and power factor) which will result when the new motors are placed in service and certain older motors are withdrawn from service. Electric loads are tabulated in section 4.0 for each area for present conditions, the planned changes and the post-CG-558 conditions. The reduction of distribution voltage during the starting of individual 4500 hp synchronous motors. Since the synchronous motors will be started across the line as induction motors, the starting current will be high, and at a low power factor. Voltage drops are calculated for the starting of a synchronous motor, with one and then with two transformer banks paralleled. The current-interrupting capacity of switchgear vs. the maximum short-circuit current which could occur with separate transformers and with two primary transformers in parallel.

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.

Memorandum presenting the subsonic and transonic longitudinal handling qualities of the Douglas D-558-II research airplane with several wing modifications designed to alleviate swept-wing instability and pitch-up. The airplane configurations investigated included the basic wing configuration and two wing-fence configurations in combination with retracted, free-floating, or extended slat,s and a wing leading-edge chord-extension configuration.

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.

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.

The Bevatron is still undergoing a process of gradual improvement to increase both the magnitude of the beam and the reliability. The operating conditions for optimum adjustment at the present stage of development are summarized.

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Memorandum presenting wind tunnel tests performed on a family of missiles. This paper summarizes some of the performance and stability and control characteristics of the missiles.

From Introduction: "Range in more or less steady level flight depends directly on aerodynamic lift-drag ratio at high supersonic speeds, just as it does at lower speeds. This result follows from the classical Breguet range equation in the case of powered flight, and it may be easily deduced from the equations of motion for unpowered or gliding flight (see refs. 1 and 2)."