"Two short turbojet combustors designed for use with vaporized hydrocarbon fuels were tested in a one-quarter annular duct. The experimental combustors consisted of many small "swirl-can" combustor elements manifolded together. This design approach allowed the secondary mixing zone to be considerably reduced over that of conventional combustors" (p. 1).

The purpose of this report is to present results of an experimental program directed toward determining the degree of protection offered by the Panellit protection system to flow losses to a single process tube containing I & E fuel elements in K reactor.

This document provides the conclusions and recommendations of the study of purging of surface condenser tubes. (FI)

None

A direct means of monitoring and indicating the neutron flux in a reactor core is required to maintain neutron-flux equilibrium and to eliminate hot spots, flux peaking and flux oscillations. This report presents operating specification for an in-core flux monitor. The specifications are based upon the recognized requirements and operating characteristics for Hanford reactors and are presents as the criteria for development, application, and evaluation of prototype in-core flux monitor systems.

A series of cutaneous burns was produced on swine by exploding 150 mgm of magnesium powder at distances of 20 and 25 cm from the animal. This provided 20 cal/cm/sup 2/ at exposure times of 0.7 and 2 to 3 sec and 16 cal/cm/sup 2/ at an exposure time of 0.7 sec respectively. The effect of placing green and khaki poplin fabrics untreated and treated with fire-retardant material L-S 123P, in contact with and separated 5 and 10 mm from skin was studied. Burns were evaluated both by surface appearance and by microscopic examination. All the fabrics reduced the severity of the burns. As the amount of separation increased, the severity of the burns decreased if the fabric remained intact. The knaki fabric with its higher reflectance gave more protection than the green fabric at 16 cal/cm/sup 2/ at 0.7 sec exposure time and 20 cal/cm/sup 2/ at 2 to 3 sec exposure time, but not at 20 cal/cm/sup 2/ at 0.7 sec exposure. The fire- retardant treated material gave more protection than the untreated material if it persisted longer during the exposure. If both persisted during the exposure but flaming or flaring occiirred, the untreated fabric gave more protection …

When burns are produced by a total radiant exposure of 5 cal/cm(sup 2), burn severity decreases with thermal pulses of longer duration. Maximum damage results from a pulse simulating that of a 20 KT weapon, the shortest pulse investigated; 40 KT and l00 KT weapon pulses show similar effects; and the 1000 KT pulse produces less damage. Burn severity is nearly the same from 10 cal/ cm(sup 2) whether the thermal pulse simulates 20 KT, 40 KT, 100 KT, or 1000 KT weapons. Less damage is caused by 10 cal/cm(sup 2) when it is delivered with a l0,000 KT simulated pulse. There is surprisingly little difference in the range of severity of burns from l5 cal/ cm(sup 2) when the thermal pulse simulates 100, 1000, and 10,000 KT weapons. Most of the burns from radiant exposures of 20 cal/ cm2 show complcte destruction of the full thickness of dermis. If there is a difference due to the type of thermal pulse, it is that the l00 KT pulse results in less dannage than does either the 1000 or l0,000 KT pulse. When the radiant exposure is sufficient to produce some dermal damage but not great enough to destroy the full …

Report discussing an investigation of the stability of a series of flared-body and blunted-cone models at a range of Mach numbers. Increasing the flare length was found to increase static stability and the damping in pitch. The Reynolds number was found to have a large effect on static stability at lower Mach numbers, but little effect on the higher end of the range covered in testing.

Memorandum presenting the results of recent exploratory investigations of the performance of clustered jet-exit installations at Mach numbers from 0.60 to 3.05. Data presented in this report were obtained with tunnel-wall-mounted models with cold-air-jet exhaust. Results regarding base pressures, effect of boattailing, effect of afterbody-nozzle geometry, and terminal fairings are provided.

Memorandum presenting a study of the static stability and control problems associated with several hypersonic boost gliders. Generally, it is possible to obtain the desired trim features. Results regarding the high-lift-drag-ratio type of gliders and low-lift-drag-ratio type of gliders are provided.

Memorandum presenting an investigation of the performance of a semielliptical scoop inlet with a two-dimensional flow field at the design Mach number of 2.0. The investigation included a study of the effects of inlet-leading-edge shape and boundary-layer bleed on the pressure recovery and total-pressure distribution. Results regarding performance of inlets without boundary-layer bleed, effect of diverter boundary-layer bleed, effect of leading-edge sweep angle, effect of compression-surface bleed, performance of inlet III-B, tests of buzz suppressors, and tests of rearward-facing control tubes are provided.

Recent experience with liquid hydrogen bubble chambers of 25 and 40 cm dia. in high-energy physics experiments is discussed. Experiments described are: interactions of K/sup -/ mesons with prctons, iateractions of antiprotons with protons, catalysis of nuclear fusion reactions by muons, and production and decay of hyperons from negative pions. (W.D.M.)

There have been numerous independent suggestions to use high speed shocks to heat deuterium gas to thermonuclear temperature (E. Teller, R.R. Wilson, H. Grad, W. Marshall)², and extensive experimental work in this field is being carried on by, e.g., Kolb³, and S. Janes⁴. Our own work in this field has been directed towards a fundamental understanding of the strong shock process in the limit of no particle collision, to find out if within this limit the ion heating following the passage of the shock is large enough to give rise to a thermonuclear reaction.

This report presents Hydraulics Laboratory data of the pressure drop characteristics for various combinations of ``pierced-solid`` dummy slugs in the support charges in the K, BDF, and C reactor process tubes. ``Pierced-solid`` slugs are regular solid aluminum dummy slugs which have been concentrically drilled so that mating against an I and E slug would not block the hole flow channel. No operating peculiarities were observed while using ``pierced-solids`` in the support charge.

Abstract: During March 1958, representatives of the health and Safety Laboratory, New York Operations Office, visited Columbia University to make stray radiation measurement at the Van de Graff accelerator. A radiation survey was performed at the Van de Graaff electrostatic generator at Columbia University. The survey results do not indicate a particular need for additional shielding at this time. It is recommended that the analyzer area of the beam room should not be occupied during beam operations and the present interlock system should be modified by the installation of a photocell interlock as shown on the included plan.

Introduction: This report is principally concerned with analysis of measurements taken on the APPR-1 core during the course of the extended Zero Power Experiments (ZPE-2). The bulk of these measurements are reported in APAE No. 21. There are some additional measurements reported in APAE Memo 115. In addition to the analysis of the ZPE-2 data some re-evaluation has been made of a few of the results obtained from the first set of Zero Power Experiments (ZPE-1). The ZPE-1 measurements are reported in APAE No. 8. During the course of analysis work it became apparent that a considerable amount of basic experimental data had been taken on the APPR-1 core. It seemed worthwhile to organize this report in such a fashion that other investigators could make maximum use of this data. It provides excellent opportunity for individuals and groups interested in basic reactor reactor analysis problems to check calculational techniques. An attempt has been made to include all of the fundamental information concerning the material content and geometry of the APPR-1. This material is in included in the Appendices. In addition, cross-section files and group constants have been listed rather extensively in order that other investigators could compare results presented in …

Report presenting the aerodynamic characteristics of a new type of lateral control through a range of Mach numbers. The control consisted of airfoils mounted vertically at the tips of the wing and could be rotated to induce rolling moments or lift on the wing surface. Results regarding lateral-control characteristics and lift-control characteristics are provided.

Report presenting an investigation of the performance of clustered jet-exit installations at Mach numbers from 0.60 to 3.05. The data were obtained with tunnel-wall-mounted models with cold-air-jet exhaust. Results indicated that large base-pressure drag coefficients may be encountered in the transonic and low supersonic speed range and that the best configuration in the test was boattailed between the nacelles, had a cylindrical nacelle afterbody, and a divergent nozzle with a design pressure ratio of 15.

Report presenting an investigation of some effects of Reynolds number on the stability of a series of flared-body and blunted-cone models at a range of Mach numbers in three wind tunnels. The Reynolds number had a pronounced effect on the static stability of the flared-body models at the lower Mach numbers. Results regarding the static stability and damping in pitch are provided.

Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41 and 2.01 to determine the stability and control characteristics of a canard-controlled airplane configuration with potentially high values of lift-drag ratio. The configurations investigated included a plane and a twisted wing with approximately 67 degrees of sweep and an aspect ratio of 2.91 and three trapezoidal canard surfaces with ratios of exposed area to wing area of 0.032, 0.076, and 0.121.

Report presenting an investigation on canard airplane configurations in preference to a trailing-edge flap or tail control. Wide ranges in control plan form, size, and position and in wing plan form were found. Interference effects between the canard and other configuration components were not serious, and those that might be can be reduced by rearrangement of the vertical tail.

Report presenting testing on the effective heats of ablation of a number of materials using supersonic arc jets at stagnation temperatures ranging from 2000 degrees F to 11,000 degrees F. Materials examined included Teflon, nylon, Lucite, polystyrene, ammonium chloride, sodium carbonate, several phenolic resins, and melamine-fiber glass laminate.

Memorandum presenting an investigation of the distortion removal performance and associated total-pressure-loss characteristics of several freely rotating fans, three single-stage and two double-stage freely rotating fans over a range of radial and circumferential distortions of from 0 to 20 percent at inlet annulus Mach numbers from 0.30 to about 0.60. Results regarding individual fan performance, comparison of fan distortion removal characteristics, and fan total-pressure loss and operating speed characteristics are provided.

"A program was conducted in an altitude facility at the NACA Lewis laboratory to investigate the effects of rapid inlet pressure oscillations on the operation of a current turbo jet engine. These pressure oscillations were approximately sinusoidal in form and were generated to cover a frequency range of 2 to 75 cycles per second and an amplitude range of 10 to 70 percent of the free-stream total pressure. As the oscillation progressed through the compressor, the amplitude was attenuated considerably and a relatively large phase shift (lag) occurred" (p. 1).