The following document describes data collected from a 14-month period of analyzing crustaceans containing radioactivity. Provided is information based on the change of radioactivity through seasonal changes.

"An investigation has been made in the Langley 4-by-4-foot supersonic pressure tunnel to determine the aerodynamic characteristics of a series of missile configurations having low-aspect-ratio wings at a Mach number of 2.01. The effects of wing plan form and size, length-diameter ratio, forebody and afterbody length, boattailed and flared afterbodies, and component force and moment data are presented for combined angles of attack and sideslip to about 28 degrees. No analysis of the data was made in this report" (p. 1).

Memorandum presenting the pressure recovery, mass flow, and axial force of four bodies with nose inlets measured at Mach numbers between 1.4 and 2.0 and angles of attack of 0, 3, 6, and 9 degrees. The drag coefficients of axially symmetric diffusers operating at the maximum mass-flow rates were calculated from schileren photographs of the head shock waves and frictional drag considerations. Results regarding open-nose diffusers and conical-shock diffusers are provided.

The non-project literature concerning the chemistry of vanadium has been summarized through November, 1952. The report is presented in terms of izo- and heteropoly vanadates and cationic forms of pentavalent vanadium, complexes of di-, tri-, and pentavalent vanadium, and oxidation potentials of various vanadium systems. A bibliography of 93 references is included.

The following report covers a test with the objective to demonstrate that the plutonium and uranium losses associated with the aluminum jacket dissolution could be reduced by substituting a water wash for the 5 per cent nitric acid wash following the coating removal and that this change would not adversely effect the product yield of decontamination in subsequent process steps.

It has been observed that energetic gaseous ions mark their region of impingement on certain metals in color. Under identical conditions of bombardment, multicharged ions of the same gas mark their impact areas with different colors. The colors are sensitive to the type and energy of the ion as well as to the metal bombarded. These colors may result from reflections from thin films formed by reactions at the target. Because the colors indicate that thicker films are produced with increased ion energy, ion penetration depth as predicted by theory is compared with the depth indicated by the colors observed.

Report presenting the effect on drag of varying the vertical position of a nacelle at 40 percent semispan of a 45 degree sweptback wing and body combination as determined by transonic flight tests at zero lift. Three nacelle positions were investigated: a pylon mounted nacelle, an underslung nacelle, and a symmetrically mounted nacelle. Results regarding total drag coefficient and maximum wing-tip helix angle are provided.

This report is a record of experimentation conducted intermittently over a period of two years and directed toward preventing deposition of transport corrosion products on fuel elements and other critical components in high-temperature, circulating water nuclear reactor. It includes the postulated mechanism for deposition, a description of experimental equipment, experimental data, results obtained from the experiments, and recommendations for future study.

"Aerodynamic data have been obtained for a 45-degree sweptback wing-body-canopy configuration at transonic speeds with the canopy placed on the body so that the cross-sectional area of the canopy approximately filled the concave portion of the basic wing-body cross-sectional-area distribution curve (design location) and with the canopy placed 0.0614 of the body length forward of the design location. Data have also been obtained for the basic wing-body combination. Placing the canopy in the rear position significantly reduced the drag of the configuration at transonic speeds, increased the lift, and did not appreciably affect the slope of the pitching-moment curve" (p. 1).

Memorandum presenting tests in the 9-inch supersonic tunnel of three bomb or store shapes without fins and with two sets of cruciform fins. Measurements of normal force, chord force, and pitching moment were made; analyses of the effects of angle of attack and Reynolds number on these qualities and also upon center-of-pressure position and fin effectiveness are presented.

The power and estimated reprocessing load are tabulated for existing and proposed United States and United States-built reactors of 10 Kw or greater thermal power.

Memorandum presenting an exploratory investigation conducted to determine the performance characteristics of a fuel-rich hydrogen combustor; in addition, the performance of an afterburner operating with the fuel-rich exhaust mixture was evaluated. Results regarding performance of the fuel-rich combustor, afterburner performance, and resonating combustion are provided.

Report presenting results and analysis of the longitudinal stability and control characteristics of the Douglas D-558-I airplane at a range of altitudes and Mach numbers. It was found that large and rapid changes in elevator deflection and force were required for balance at Mach numbers above 0.84 due to a sharp decrease in elevator-stabilizer effectiveness.

Flight tests were conducted at the Flight Test Station of the Pilotless Aircraft Research Division at Wallop Island, Va., to determine the longitudinal control and stability characteristics of 0.5-scale models of the Fairchild Lark pilotless aircraft with the tail in line with the wings a d with the horizontal wing flaps deflected 60 deg. The data were obtained by the use of a telemeter and by radar tracking.

From summary: "In order to estimate the effect of placing bismuth and thorium layers near the MTR core, radial flux distributions and k[infinity] values were calculated for cylindrical reactors having cylindrical layers of these materials of the same height as the core and beryllium reflector and placed either next to the core or embedded in the beryllium reflector."

Technical report covering the work done to explore heat transfer analytically and experimentally in liquid metals in turbulent flow within the thermal entrance region of circular tubes having uniform well temperature. Includes implications of this research. [From Summary]

Report presenting the results of force and moment tests at Mach numbers from 3.0 to 6.3 on bodies of revolution of fineness ratios from 5 to 10 and on flat-bottom bodies of fineness ratio 10 along with theoretical predictions for these bodies. Testing included eight cone and cone-cylinder models, six nose-cylinder models, and three flat-bottom bodies.

Evaluation of the conditions under which the interaction effects of two or more sub-critical quantities of enriched uranium may be safely arranged.

Memorandum presenting an investigation to evaluate the effect of Reynolds number and Mach number on the aerodynamic characteristics of a horizontal tail of aspect ratio 3 equipped with a plain, sealed, full-span elevator. The line joining the quarter-chord points of the airfoil sections was swept back 45 degrees and the sections perpendicular to this line were the NACA 64A010. Results regarding the effect of Reynolds number and effects of leading-edge roughness and elevator-nose seal are provided.

Report presenting an investigation of the low-speed power-on stability and control characteristics of a free-flying model of the North American X-15 airplane. Results regarding the longitudinal stability and control, lateral stability, and lateral control are provided. Longitudinal stability was low, but it was considered to be satisfactory up to an angle of attack of about 30 degrees.

Technical report. From Introduction : "The nuclear volume dependent isotope shift of optical spectral lines has long been a very useful means for studying the changes in the nuclear size or shape for different isotopes of heavy elements."

Report issued by the Oak Ridge National Laboratory discussing revisions to previously issued conversion coefficient tables. The revised tables are presented. This report includes tables, and graphs.

Quarterly report of the Chemistry Division at the University of California Radiation Laboratory providing updates for each department about current findings and ongoing research.

Report presenting drag coefficients determined by the accelerometer method for the Bell X-1 airplane with 8-percent-thick wing and 6-percent-thick tail in power-off flight over a range of Mach numbers and lift coefficients. Results regarding the variation of computed lift and drag coefficients, variation of lift coefficient with Mach number, and effect of Mach number on lift-drag ratio are provided.