Introduction: "A laboratory investigation of the relative corrosion resistance of several austenitic stainless steels to the RAW stream of the Tributyl Phosphate Waste Metal Recovery Process was made during the first quarter of 1950. The results of this investigation are reported herein; all original data are recorded in laboratory notebook HW-3282-T."

Purpose and scope: The purpose of this report is to present an analysis and evaluation of the airborne radioactivity survey of the Blanding, Utah district conducted by The Texas Company on behalf of the Atomic energy Commission. Within the scope of the report, only the results of the airborne survey and the data used in its evaluation are presented. No attempt is made to discuss the details of the survey or of the drilling program conducted in the area. A separate report by P. 1. Melanoon, on the drilling program is in preparation.

Report presenting lift, drag, and pitching-moment coefficients, lift-drag ratios, and center-of-pressure positions for four airplane-like configurations determined from tests at a range of Mach numbers and angles of attack. The wings and nose shapes were modified for each of the configurations.

Report presenting flight measurements of the pressures on the horizontal tail surfaces of a typical propeller-driven pursuit airplane during stalled pull-outs at high Mach number. Unit loads measured on the stabilizer at safe maneuvering limits were not only considerably in excess of the design unit loads, but also occurred in a direction opposite to the design loads. Revision of the tail-load design requirements and manner of specifying safe maneuverability limits to pilots appears necessary.

Report presenting the results of oscillation tests to measure the dynamic-rotary stability derivatives of an airplane model at high subsonic speeds. Measurements taken included the damping in pitch, damping in yaw, damping in roll, and the yawing moment due to rolling velocity.

"Model investigations were made to determine the ditching characteristics of three typical multiengine airplanes equipped with possible arrangements of hydro-ski ditching gear. The behavior of the models was determined from visual observations, acceleration records, and motion pictures of the landings. Data are presented in tabular form and sequence photographs" (p. 1).

Report presenting an investigation of aileron flutter associated with high-speed flight. When the aileron control system was modified by installing a hydraulic irreversible unit, it was possible to delay aileron flutter and reduce its amplitude. Results regarding the aileron flutter with and without the modifications, analysis of the time histories for the control systems, and relation between aileron upfloat and flutter are provided.

Report discussing an investigation of the effect of spanwise aileron location on the rolling effectiveness of plain faired ailerons on untapered wing plan forms with designated sweep, airfoil sections, and aspect ratio using rocket-propelled test vehicles. Drag data is also presented for all configurations tested. Spanwise aileron location was found to have little effect on the effectiveness of the aileron on an unswept wing plan form.

Report presenting the results of pressure-distribution tests to determine the effects of compressibility on the characteristics of the NACA 66,2-215, 66,2-015, 65(216)-418, 16-212, and 23015 airfoil sections. Schileren photographs of the air flow and data on the wake characteristics was also obtained.

Memorandum presenting an investigation of two annular diffusers of different conical angles of expansion but constant outer diameters with rotating flow behind a fan. The performance characteristics are determined and the rotational-kinetic-energy effects on the overall energy transformation are observed over a range of inlet mach numbers from 0.1 to 0.44 and angles of flow up to 28 degrees.

Report presenting the total drag coefficients of 60 degree cone cylinders of fineness ratio 2.07 measured in free flight from Mach numbers of 1.5 to 8.2. Results regarding the smooth 60 degree cone cylinder, rifled models, and discontinuity lines in the shadowgraph pictures are provided.

Report presenting an investigation of the drag of spherically blunted conical models of fineness ratio 3 at a range of Mach and Reynolds numbers. Results of the tests showed that slightly blunted models had less drag than cones of the same fineness ratio through the Mach number range. Results regarding the total drag, wave drag, and viscous effects are provided.

From Introduction: "Because of the unusual nature of this equipment, and because it is proving to be very useful for certain kinds of aerodynamic research, this report has been prepared. It contains a description of the equipment and its use to obtain aerodynamic coefficients. The imperfections in the wind-tunnel air stream and their effect on model tests are also discussed."

Memorandum presenting the pressure recovery, mass flow, and drag of a twin-scoop, side-inlet-body combination measured at Mach number 1.4 and 1.7. The inlet was located on a body having an ogival nose followed by a cylindrical section and a total fineness ratio of 5.

Report presenting an investigation to determine the ditching characteristics of three typical multiengine airplanes equipped with different arrangements of hydro-ski ditching gear. The behavior was determined from visual observations, acceleration records, and motion pictures of the landings. Results regarding ski size, shape, and location are provided.

The results of an investigation of two 10-foot-diameter, two-blade NACA propellers are presented for a range of blade angles from 20 degrees to 55 degrees at airspeeds up to 500 miles per hour. These results are compared with those from previous investigations of five related NACA propellers in order to evaluate the effects of blade-section thickness ratios on propeller aerodynamic characteristics.

"A general algebraic method of attack on the problem of controlling gas-turbine engines having any number of independent variables was utilized employing operational functions to describe the assumed linear characteristics for the engine, the control, and the other units in the system. Matrices were used to describe the various units of the system, to form a combined system showing all effects, and to form a single condensed matrix showing the principal effects. This method directly led to the conditions on the control system for noninteraction so that any setting disturbance would affect only its corresponding controlled variable" (p. 581).

From Introduction: "Numerous tests of tip controls on delta wings at transonic and low supersonic speeds have shown that such configurations provide satisfactory rolling-moment effectiveness, and that the hinge can be controlled by proper location of the hinge line (ref. 1). The purpose of the present tests is to determine the characteristics of such a configuration at Mach number of 4.04 and a Reynolds number of 5.8 X 10^6, based on the wing mean aerodynamic chord."

Report presenting an investigation of a configuration of a body of fineness ratio 16.9, an unswept wing of aspect ratio 3, and a taper ratio of 0.4, and incline tail surfaces who was aeropulsed continuously in pitch during free flight with and without a sustainer rocket motor operating. A range of Mach numbers from 0.8 to 2.1 was tested. Results regarding drag, normal force and pitching moment, flow conditions at the horizontal tail, buffeting and model vibrations, and cross coupling are provided.

Abstract: This is a selective bibliography of books and periodical articles relating to radioactive waste disposal. Material in the bibliography is concerned primarily with methods for the handling and disposal of wastes and the results of these methods. Auxiliary material indicating methods of determining radioactivity in wastes has been included. Sources consulted include: Chemical Abstracts, 1950-1955; Engineering Index, 1950-1955; Industrial Arts Index 1950-March 1957; Nuclear Science Abstracts, 1950-March 15, 1957; Physics Abstracts, 1950-1955; the Library card catalog; and the Technical Information Division AEC card catalog.

The following report records measurements and evaluations of fast neutron levels in remote areas monitored by personnel.

The status of research is reviewed in a study of pulmonary granulomatosis in beryllium workers. Equipment for use in dust exposure studies is described. Preliminary results are reported from studies on the tissue distribution and pathological effects of beryllium dust in rats; the physical chemistry of solutions of beryllium salts; the effects of beryllium on enzyme systems, and the effects of ascorbic acid on beryllium excretion.

The following report follows a correction on a previous report (CP-1381) on the value of the magnitude of the gamma effect.

The study was undertaken with the objective of observing the distribution in the rat of organic compounds of phosphorus labelled with the P32 isotope as tracer. The fate of several of these compounds was studied in animals bearing tumors. The distribution of inorganic phosphate in animal tissues is well known but was included in this work for comparison with the organic phosphorus compounds.