From introduction: "In this report we consider a few non-adiabatic processes. The types to be discussed will be limited because of two reasons: first, complete descriptions are available for some processes; second, as time goes on alternative injection methods undoubtedly will be discovered, so this list must necessarily be incomplete."

Technical report that attempts to bring together the various chemical procedures which proved most useful in studying the results of cyclotron bombardment or small scale neutron bombardments of heavy element targets. The report is limited to the elements of the "actinide", or second rare earth series, starting with thorium and including the newly discovered elements of atomic number 95 and 96. Every attempt is made to include all details necessary so this report can serve as a practical laboratory guide. The report covers separation problems, time factors, and dealing with dangerously radioactive targets.

Memorandum presenting the results of an investigation of the stability, control, and induced rolling moments of a canard missile with cruciform wings of rectangular plan form at Mach number 1.7. All data including the measured hinge moments of the canard control surfaces, the axial forces on the complete missile, and the forces and moments on the various combinations of the missile components are presented in tabular form.

Memorandum presenting the effect of blunting on the internal performance of a two-cone inlet with an internally cylindrical cowl investigated experimentally at Mach number 4.95. Total-pressure-recovery and mass-flow data were obtained for a range of spike and cowl bluntness.

Report presenting an investigation of the effect of inlet component blunting on performance using an axisymmetric external-compression inlet in the supersonic wind tunnel. The investigation was carried out to determine the performance penalties associated with spike-tip and cowl-lip blunting. Results regarding the effect of rounding the spike tip on inlet performance, overall drag coefficients, flow distortion, and Schileren photographs are provided.

"A rocket of the 1000-pound-thrust class using liquid oxygen and JP-4 fuel as propellant was installed in the Lewis 8- by 6-foot tunnel to permit a controlled study of some of the factors affecting the heating of a rocket-missile base. Temperatures measured in the base region are presented from findings of three motor extension lengths relative to the base. Data are also presented for two combustion efficiency levels in the rocket motor" (p. 1).

"Investigation of the control parameters of an external-internal compression inlet indicates that the cowl-lip shock provides a signal to position the spike and to start the inlet over a Mach number range from 2.1 to 3.0. Use of a single fixed probe position to control the spike over the range of conditions resulted in a 3.7-count loss in total-pressure recovery at Mach 3.0 and 0 deg angle of attack. Three separate shock-sensing-probe positions were required to set the spike for peak recovery from Mach 2.1 to 3.0 and angles of attack from 0 deg to 6 deg" (p. 1).

Report presenting an investigation of the pressure distributions over the drooped-nose flap of a 42 degree sweptback wing with circular-arc airfoil sections and half-span trailing-edge split flaps in the 19-foot pressure tunnel. The effects of the deflection and span of the drooped-nose flap and effects of split trailing-edge flaps on the pressures over the drooped-nose flap were determined.

Report presenting an altitude-chamber investigation to determine the altitude performance characteristics of the British Rolls-Royce Nene II turbojet engine with a standard 18.75-inch-diameter jet nozzle. Results regarding the simulated flight performance and generalized performance across other altitude and pressure characteristics are provided.

Memorandum presenting an investigation in the 9-inch supersonic tunnel of several missiles with low-aspect-ratio, cruciform, tandem lifting surfaces with a view toward developing a missile with small variations of center-of-pressure location at various angles of attack and roll. The investigation centered about a basic configuration with equal-span wings and tails.

Memorandum presenting the results of an investigation of the stability, control, and induced rolling moments of a canard missile with cruciform wings of rectangular plan form at Mach number 1.7. All of the data obtained, including the measured hinge moments of the canard control surfaces, axial forces on the complete missile, and forces and moments on the various combinations of missile components are presented in tabular form.

Report presenting an investigation of the aerodynamic loads on a leading-edge slat on a 40 degree sweptback wing with NACA 64(sub 1)-112 airfoil sections in the low-turbulence pressure tunnel. Results regarding wing force data, slat force data, and slat pressure distributions are provided.

Report presenting an investigation in the free-flight tunnel to determine the dynamic lateral stability and control characteristics of a high-aspect-ratio bomber model with a sweptback-wing fighter model attached to each wing tip with freedom in roll. The results indicated that the longitudinal position of the fighters with respect to the bomber had an important effect on the flight behavior of the coupled configuration.

Report presenting the results of a flight investigation of the lateral stability and control characteristics of a high-speed fighter airplane. Results regarding the control-free lateral oscillations, sideslip characteristics, rudder control characteristics, rudder hinge-moment characteristics, and rolling characteristics are provided.

"The stability derivatives valid for a limited range of supersonic speeds are presented for a series of sweptback wings tapered to a point with sweptback or sweptforward trailing edges. These wings were derived by modifying the trailing edge of a basic triangular wing so that it coincided with lines drawn from the wing tips to the wing axis of symmetry. The stability derivatives were formulated by using the pressure distributions previously obtained for the basic triangular wing for angle of attack, constant vertical acceleration, sideslip, pitching, rolling, and yawing" (p. 411).

Discussing peaceful applications of nuclear explosions

Abstract: "This report includes details of the procedure along with the die and equipment descriptions for preparing tungsten copper alloy pieces."

Task A: Modification and Preparation of Experimental Facility. With the exception of the insulation of modified components, the experimental facility is complete. Insulation will be completed by the end of September. the system has been charged with Refrigerant-22 and preliminary loop performance tests have been completed without the test sections.. Task B: Design and Construction of Test Sections. The stainless steel test section has been prepared complete with end flanges and pressure tap locations. Wall thickness tolerances have been ultrasonically checked. Test section inlet and discharge assemblies are being completed and the whole assembly will be ready for installation by the end of September. Glass sections from the same drawn length which will make up the final test sections have been received for pressure tests. The final coated sections and the associated inlet and discharge fittings will be ready for assembly by the end of September. The above sections were ordered after complete preliminary tests defined the properties required of these test sections. Task C: Design and Construction of Test Stand: The mechanical design and drafting of the structural components and drive system is complete. The electrical control system for the platform orientation has been constructed and two modes of …

The Plutonium Recycle Test Reactor is a research and development tool supporting the Plutonium Recycle Program and the research activities at Hanford. The present organization directly associated with the PRTR is composed of Operating, Technical Assistance, Maintenance, and Engineering Groups. Liaison with research groups utilizing PRTR facilities is accomplished through the Technical Assistance Group. the other three groups serve the PRTR in the manner suggest by the group name. This paper limits its interest to the staffing experience of the Operating Group.

A report on the safety rules for the installation and maintenance of electric supply and communication lines.

"The studies of this report were made to indicate the thermal stability at elevated temperatures of fluorocarbons similar to the hexadecafluoroheptane" (p. 4).

Discusses habits, economic status, morphology, variation, history, and specimens of North American rice rats. Provides a key and descriptions for species and subspecies.

Report presenting an investigation in the altitude test chamber to evaluate several afterburner configurations on the XJ79 engine. Data were obtained from nine configurations which show the effect on burner performance of increased burner diameter and modifications to the flameholder, fuel system, and flow swirl.

"Measurements were made, in dives to transonic speeds, of the static-pressure position error at a distance of one chord ahead of the McDonnell XF-88 airplane. The airplane incorporates a wing which is swept back 35 deg along the 0.22 chord line and utilizes a 65-series airfoil with a 9-percent-thick section perpendicular to the 0.25-chord line. The section in the stream direction is approximately 8-percent thick. Data up to a Mach number of about 0.97 were obtained within an airplane normal-force-coefficient range from about 0.05 to about 0.68" (p. 1).