The report summarizes results obtained since September, 1951, by total neutron yield experiments using 190 Mev deuterons and the MnSo4 tank method (UCRL-1375 and UCRL-1480). A new method of beam monitoring has resulted in establishing firmly the absolute yield for solid uranium and thorium primary targets backed by a solid uranium secondary. The beam monitoring was done by using a primary target built into a faraday cup. This method circumvents errors caused by recombination in the ionization chambers used previously.

Report presenting an investigation of the effects of three centrally mounted wing-tip tanks on the aerodynamic characteristics of a cambered wing with an aspect ratio of 10 and 35 degrees of sweepback. Testing occurred over a range of Mach and Reynolds numbers and lift, drag, and pitching-moment were measured.

Report presenting the results of a series of exploratory flights on a 35 degree swept-wing airplane up to Mach number 1.09 to show the effects of compressibility on imposing maneuverability limits. Results regarding the maneuvering accelerations and buffet boundary are provided.

The following report describes data from the continuation of investigations which led to the observation and characterization of five artificial radioactive chains collateral to the natural radioactive families that has lead to the partial identification of one additional chain, collateral to the actinium family.

Memorandum presenting a discussion of the strategic-material problems of airplane engines as a whole, especially as related to parts of the engine that are not the disk or blades. Several possible approaches to the material-conservation problem are presented, including the advantages and disadvantages, and the relative gains that might result from one, or combination of a number, of these approaches.

The effects of mass-flow ratio on the additive drag and normal-shock position of a single oblique-shock diffuser are presented. Also evaluated is the variation with operating condition of the velocity distribution at the combustion-chamber inlet. A comparison with connected-pipe data is included.

A report of quarterly results of research and development directed towards establishing new techniques and instruments towards improving present methods for determining levels of radioactivity accurately and safely.

Report documenting the suitability of Arkansas for plant locations to produce synthetic liquid fuels, based on raw materials such as coal, natural gas, oil shale, and oil-impregnated strippable deposits.

"The significance of additive drag is discussed and equations for determining its approximate value are derived. Charts are presented giving values of additive drag for open-nose inlets and for annular-nose inlets with conical flow at the inlet. The effects of variable inlet total-pressure recovery and static pressures on the center body are investigated, and an analytical method of predicting the variation of pressure on the center body with mass-flow ratio is given" (p. 1).

"By use of an approximate equation for the wave drag of slender bodies of revolution in a supersonic flow field, the optimum shapes of certain boattail bodies are determined for minimum wave drag. The properties of three specific families of bodies are determined, the first family consisting of bodies having a given length and base area and a contour passing through a prescribed point between the nose and base, the second family having fixed length, base area, and maximum area, and the third family having given length, volume, and base area. The method presented is easily generalized to determine minimum-wave-drag profile shapes which have contours that must pass through any prescribed number of points" (p. 1).

Memorandum presenting an investigation of the torsion creep-to-rupture properties on the alloy steel N-155. Rupture times in the 10-to-1000-hour range were considered and tests were made at the temperatures 1200, 1350, and 1500 degrees Fahrenheit. Comparisons of the effects of simple combined stresses were made with tension creep-to-rupture properties.

Report presenting a flight investigation of an NACA hinge-moment roll research model with a sharp-nosed cylindrical body with a cruciform arrangement of 60 degree sweptback delta wings, two of which had half-delta tip controls. Data presented includes the variation with mach number of damping-in-roll coefficient, aileron rolling-moment coefficient, lateral-control effectiveness, and hinge-moment coefficient at various deflections. The rolling effectiveness of this configuration was found to be very satisfactory for a range of speeds.

An experimental investigation of a highly loaded two-stage turbine with a downstream stator revealed that (1) at equivalent design work and speed the brake internal efficiency was 0.81 and the maximum efficiency obtained was 0.85, and (2) the downstream stator left very little energy in the form of tangential velocity in the gas and, in general, performed well with 0.78 recovery being obtained at equivalent design work and speed.

"As a portion of an over-all performance investigation of the prototype J47D (RX-1) turbojet engine, performance of the compressor, combustor, and turbine components has been determined in the Lewis altitude wind tunnel over a range of altitude from 5000 to 55,000 feet and at flight Mach numbers from 0.19 to 0.92. Investigations were conducted with the engine operating on an electronic control schedule and slow with a two-lever control system by which fuel flow and exhaust-nozzle area could be controlled separately. Two combustor configurations were investigated" (p. 1).

From Summary: "Component and over-all performance characteristics of several turbojet engines investigated in the altitude facilities of the NACA Lewis Laboratory during the last several years are summarized to indicate the effects of altitude on turbojet engine performance. Data presented show that failure of turbojet engine performance to generalize for all altitudes can be traced to reductions in compressor efficiency, corrected air flow, and combustion efficiency at altitude. In addition, it is shown that although engines of different design may have equal thrusts at sea level, the thrusts at altitude may vary widely because of differences in compressor performance characteristics from one engine to another."

Report presenting a determination of control-surface flutter derivatives for a sinusoidally oscillating control surface mounted on a two-dimensional fixed airfoil for a range of reduced frequency. Results regarding subsonic results and transonic results are provided.