This quarterly progress discusses the ongoing work at the Oak Ridge National Laboratory for the quarter ending in March 10, 1952. Topics discussed include reactor theory and design, shielding research, materials research, and includes appendixes with supplemental information.

From Introduction: "This report presents the results of an analysis to determine the coolant flow and pressure requirements for a particular return-flow turbine rooter blade design utilizing hydrogen, helium, or air as the coolant."

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 …

When water is used as a coolant in any heat-producing process, the purity of the cooling water is of considerable importance, both from the standpoint of build-up of deposited solids inside the cooling tubes, and as an indication of corrosion of the tubes or any other materials with which the water comes in contact. The first problem has long been recognized, and is generally solved by pretreatment of the water. Efficient treatment can reduce the total solids content to less than 0.1 ppm, and the concentration of individual elements to the order of 0.01 ppm. If water of this purity is used, the analysis of the input and output stresses can result in some useful information. The input stream analysis, of course, is direct measure of the quality of the original cooling water, and frequent analysis by a reasonably fast method can be used to keep pretreatment under control. But of even greater significance is the difference in the impurity content of input and output streams. In a simple, straight-through system the difference generally will be negligible. If a closed, recirculating system is considered, however, with the coolant water circulating through the process to be cooled and then through a …

From Introduction: "This paper presents results of an analysis of shear, bending-moment, and torque loads measured on the vertical tail during rudder-step, rudder-pulse, aileron-roll, and steady-sideslip maneuvers. In order to assess effects of Mach number and altitude, the maneuvers were performed at altitudes of 15,000, 25,000, and 35,000 feet and Mach numbers from 0.49 to 0.82."

The angular distribution of fission fragments from the neutron-induced fission of several isotopes has been studied. Distributions were observed for thermal neutrons on U233 and U235, Lady Godiva leakage neutrons on U235 and U238, and 14 Mev neutrons on U233, U235, U238, Th232, and Np237. No anisotropy was observed for thermal neutron fission, whereas for Lady Godiva neutrons and 14 Mev neutrons the probability of fission along the axis of the neutron beam was determined to be higher than for fission in the orthogonal direction. Experimental results are given on pages 10 and ll.

Report presenting a friction, wear, and endurance-lift study made with bonded films of mixed oxides containing lead monoxide (PbO) as the main component. The coatings lubricated over the entire temperature range, but were far more effective from 500 to 1250 degrees Fahrenheit than at the lower temperatures. Results regarding the effect of silica additions on coating formation, determination of coating composition, effect of coating thickness on friction and wear, effect of temperature on friction and wear, and endurance properties are provided.

Memorandum presenting force tests that have been made of airplane configurations with a thin swept wing incorporating several wing-contour modifications forward of maximum thickness. Both longitudinal and lateral characteristics are provided.

Report presenting an investigation at subsonic, transonic, and supersonic speeds of the effect of lip shape on drag, pressure recovery, and mass flow of a nose-inlet air-induction system. Four lips of varying degrees of bluntness were tested on a fuselage model at a range of Mach numbers and angles of attack. Results regarding pressure recovery, net drag, and analysis are provided.

Report presenting a free-flight investigation to determine the effect of wing camber and twist at Mach numbers from 1.4 to 2.1 on the lift, drag, and longitudinal stability of a configuration with 52.5 degrees sweptback wing of aspect ratio 3, and inline tail surfaces. Results regarding drag, total normal force and pitching moment, and wash at the horizontal tail are provided.

The following report follows the studies of electroplating on uranium and concurrent metallurgical clodding.

Twelve uranium-magnesium fuel material samples have been irradiated in the MTR at the request of the Pile metallurgy Unit. These samples were 0.40 inch in diameter by 1.5 inches long and were canned in Zircalloy-2 capsules. The uranium used in these specimens was in the form of chips which packs about 50 volume percent. Six of the samples contained a matrix of pure magnesium and the other six contained an alloy matrix of magnesium - 1.4 weight percent silicon. Two specimens of each matrix material were irradiated to 1000 MWD/T and a like number to 5000 MWD/T. Bend tests were performed on the samples and on unirradiated control samples to secure a measure of the effect of radiation exposure on the physical properties of the material.

Memorandum presenting the detailed blade-element performance of a five-stage axial-flow compressor for analysis purposes as well as to provide a contribution to the growing body of information necessary for continuing improvement in designing compressors. Results regarding overall and stage performance, blade-element performance, rotor blade-element performance, stator blade-element performance, comparison with design, consideration of boundary-layer blockage effects, and solution of equilibrium equation are provided.

Testing was conducting to evaluate the effects of support interference on the drag characteristics of two bodies of revolution at zero angle of attack at Mach number 1.5. Drag and base-pressure measurements are made for a variety of Reynolds numbers to determine the effect of varying the length or diameter of the rear support.

Description of the standards used by the electrical power industry for the measurement of the electrical quantities.

From introduction: The purpose of this paper is to present the geologic facts which have been discovered thus far about the Lukachukai area and to draw conclusions about uranium mineralization. Basic data of general nature are included to facilitate the work of future geologists in this area who may find the information applicable to new ideas.

An analysis of the off-design performance of shock-in rotor-type supersonic blading is presented. The over-all losses are assumed divided into two groups;normal-shock losses, and external-wave losses. Throughout the range of relative entrance Mach numbers from 1.35 to starting, the largest losses can be attributed to the normal shock. An improvement in performance would be expected with a reduction of the normal-shock losses by the introduction of external compression waves.

Report presenting testing on 31 airfoils to determine the effects of thickness, trailing-edge bluntness, boattailing, and forward profile on the aerodynamic characteristics of thin airfoils, and to provide a check on available theoretical methods. The airfoils were 2, 4, and 6 percent thick and were tested at two Mach numbers at three Reynolds number in clean condition and one with transition fixed.

As part of a general investigation of propellers at high forward speeds, tests of two-blade propellers having the NACA 4-(5)(08)-03 and NACA 4-(10)(08)-03 blade designs were made in the Langley 8-foot high-speed tunnel through a range of blade angle from 20 degrees to 60 degrees for forward Mach numbers from 0.165 to 0.70 to determine the effect of camber and compressibility on propeller characteristics. Results previously reported for similar tests of a two-blade propeller having the NACA 4-(3)(08)-03 blade design are included for comparison.

Powered models of three different flying boats were landed in oncoming wave of various heights and lengths. The resulting motions and acceleration were recorded to survey the effects of varying the trim at landing, the deceleration after landing, and the size of the waves. One of the models had an unusually long afterbody. The data for landing with normal rates of deceleration indicated that the most severe motions and accelerations were likely to occur at some period of the landing run subsequent to the initial impact.

"This report combines the wind tunnel results of tests on four control surface models made in the two wind tunnels of the Navy Aerodynamic Laboratory, Washington Navy Yard, during the years of 1922 and 1924, and submitted for publication to the National Advisory Committee for Aeronautics May 7, 1927. The purpose of the tests was to compare, first, the lifts and the aerodynamic efficiencies of the control surfaces from which their relative effectiveness as tail planes could be determined; then the elevator hinge moments upon which their relative ease of operation depended. The lift and drag forces on the control surface models were obtained for various stabilizer angles and elevator settings in the 8 by 8 foot tunnel by the writer in 1922; the corresponding hinge moments were found in the 4 by 4 foot tunnel by Mr. R. M. Bear in 1924" (p. 429).

The following handbook was made for the purpose of: (1) to give a semidetailed description of the testing reactor, and (2) to explain, in so far as possible, the reasons for the design.

Report presenting an investigation in a mixing-zone apparatus to determine the effects of jet flow on two-dimensional base pressure and the development of supersonic channel flow about a two-dimensional base, with and without splitter plates of different thicknesses. Results regarding the starting cycle for outer streams only, the fully established supersonic flow, and the base pressure between the center jet and outer streams are provided.

Memorandum presenting a determination of the shapes of bodies with minimum pressure drag for a given lift at high supersonic speeds and satisfying conditions of given length and width with the aid of Newton's law of resistance. The resulting shapes have flat bottoms which are also rectangular. To determine if the bodies do actually have improved lift-drag ratios at high supersonic speeds, several wedges satisfying numerically different sets of given conditions were tested at Mach number 5.