The purpose of this report is to present the derivation of equations useful as a guide for prediction of the critical flow point in orifice assemblies.

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Thesis analyzing a lead-glass photon spectrometer and its use in studying the absorption of photons and antinucleons.

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This test as detailed in this report is one of three parts of the initial testing program to demonstrate enriched usage at HAPO. It proposes to irradiate two twelve-tube blocks of enriched uranium and lithium-aluminum slugs to obtain conversion ratios and preliminary information concerning slug stability.

Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 2.01 to determine the effects of the addition of four small fuselage-mounted cruciform fins on the directional characteristics of a 45 deg swept-wing airplane model at angles of attack up to 15.3 deg and angles of sideslip up to about 16 deg. The results showed that the addition of the four cruciform fins to the model increased the directional stability substantially at the highest angle of attack and, at the same time, caused relatively small changes in drag.

The heat generated by reactor fuel elements create thermal gradiants which cause thermal stresses of considerable magnitude. An elastic solution for these thermal stresses can be calculated with the equations given in Timoshenko's and Goodier's book (1) on elasticity if the fuel element is assumed infinite in length. An exact elastic solution for a finite cylindrical fuel element is given in this report in order to evaluate the effects of fuel element length on the thermal stresses and the effects of having the free end material distorting the end closure.

Memorandum presenting oscillatory hinge-moment characteristics obtained from free-flight tests of two rocket-powered models equipped with a 60 degree sweptback clipped delta wing featuring an unbalanced, constant-chord, full-span trailing-edge control. One aircraft had a control with a sharp trailing edge, and the other had a trailing-edge thickness equal to 1/2 the thickness at the hinge line. Results regarding control pulsing systems, control damping, and control restoring moments are provided.

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Memorandum presenting a review of the subsonic-diffuser data available in the literature, which is then reduced to certain appropriate performance coefficients and presented as functions of the significant geometric and flow variables. Results regarding total-pressure-loss factor, diffuser effectiveness, recovery of diffuser effectiveness in the tailpipe, inlet speed effects, exit flow distributions, boundary-layer control, and effects of distorted inlet velocity distribution are provided.

Report presenting a review of subsonic-diffuser data, which was reduced to certain appropriate performance coefficients and presented as functions of the significant geometric and flow variables. The report is divided into the following sections: performance at low speeds, the effect of increasing the inlet speed up to choking Mach numbers, illustrations of the effectiveness of boundary-layer controls, and illustrations of the effects of distorted inlet velocity distributions at subsonic speeds.

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Thermodynamic properties of hydrogen and its products of combustion with air are tabulated in a form convenient for use in cycle analysis and design of turbojet engines. Only low pressures are considered, and the effects of dissociation are ignored. Several thermodynamic processes are analyzed, and their analysis is illustrated by numerical example.

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Reactor gas costs have increased substantially each year since 1952 when the total cost was $108,000. In 1953, 1954, and 1955 the gross annual cost of reactor gas was $126,000, $348,000 and $606,000 respectively and are reported in Figure 1. These continued increases in reactor gas costs indicate the need for an analysis of gas usage and formulation of a program to reduce gas consumption. To provide basic information for such a program, a critical review has been made of the reaction gas system and gas consumption figures for the past four years.

The dependence of the resonance integral for thorium upon geometry and thorium temperature has been determined through reactivity coefficient measurements performed in the Hanford Test Pile. The geometry dependence was investigated using thorium cylinders of various diameters in the form of solid elements and shells. The temperature dependence (Doppler broadening) was studied by heating thorium elements and permitting them to cool while observing the change in pile reactivity.

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Report presenting an investigation of three phases: an experimental investigation of a thin airfoil with blowing over a trailing-edge flap, a comparison of the results of the experimental investigation with the results of other similar investigations, and a theoretical study of the relationships among the air-flow and power parameters for the general blowing case. The investigation utilized a two-dimensional model of the NACA 0006 airfoil equipped with a nose flap and six alternate trailing-edge flaps.

Changes made in the Thorex process flowsheet were a decrease in the extraction column acidity to decrease thorium losses and the addition of a second thorium solvent-extraction cycle to provide the increased decontamination required when thorium irradiated to 2000-4000 g of U233 per ton is processed. Bonded slugs could not be dissolved by the Thorex flowsheet procedure. Various laboratory scale studies on feed preparation, first-cycle variables, and radiation damage to the solvent are reported.

Report presenting an investigation of the lateral stability and control effectiveness of a model of a fighter-type airplane model with a low-aspect-ratio and 3.4-percent-thick wing with negative dihedral at a range of Mach numbers, sideslip angles, and angles of attack. Results regarding the lateral characteristics at zero angle of attack, lifting conditions, and lateral and directional controls are provided.

Report presenting the longitudinal stability characteristics of a simple infrared homing missile determined in flight with a rocket-powered model. Static and dynamic longitudinal stability derivatives of the cruciform, interdigitated, canard-wing missile configuration were determined using the pulse-rocket technique for a range of Mach numbers.

Paper presenting a preliminary account of some research conducted on the general problem of flow separation. The research is fundamental in nature, partly theoretical, and partly experimental. Measurements are made of subsonic and supersonic speeds for a variety of two dimensional model shapes involving separation.

Abstract: "The neutrons from the linear pinch in Berkeley have been shown to originate from deuteron collisions with a large net center-of-mass velocity in one direction along the axis of the pinch tube. The interpretation of this result is that the neutron production associated with the pinch is non-thermonuclear in origin. The object of this paper is to review the experimental evidence and discuss a possible source of the neutron production."