The first part of this quarterly progress report details reactor theory and design, discussing the aircraft reactor experiment, experimental reactor engineering, reactor physics, and critical experiments. The second part of this report is not included. The third part of this quarterly progress report details materials research, discussing corrosion research, physical properties and heat-transfer research, metallurgy and ceramics, chemistry of high-temperature liquids, and radiation damage. The fourth part of this quarterly progress report details alternate systems, discussing a supercritical water reactor, circulating-moderator-coolant reactors. The fifth part of this quarterly progress report includes appendixes.

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"An experimental investigation is being conducted at the Lewis laboratory to establish general principles for the design of noncritical turbine rotor configurations. This investigation includes evaluation of cooling effectiveness, structural stability, cooling-air flow distribution characteristics, and methods of supplying cooling air to the turbine rotor blades. Prior to design of a noncritical rotor, a standard turbine rotor of a commerical turbojet engine was split in the plane of rotation and machined to provide a passage for distributing cooling air to the base of each blade" (p. 1).

Memorandum presenting a supplementary investigation in the 20-foot free-spinning tunnel to determine the effect of external stores and lateral center-of-gravity displacement on the spin and spin-recovery characteristics of a scale model of the McDonnell F2H-3 airplane. Results regarding wing-tip tanks and experimental aerodynamic shapes are provided.

Report presenting an investigation in the high-speed tunnel to determine the effect of sweep on the static lateral stability characteristics of wing-fuselage combinations with wings of aspect ratio 4 and taper ratio 0.6 at high subsonic speeds. Results regarding rolling-moment characteristics and lateral-force and yawing-moment characteristics are also provided.

Report presenting a wing-body combination with a plane tapered wing of aspect ratio 3.1, taper ratio of 0.39, and 3-percent-thick, rounded-nose sections in streamwise planes at subsonic and supersonic Mach numbers. The lift, drag, and pitching moment are presented for a range of Mach numbers and Reynolds numbers.

Report presenting an investigation of the separate and combined effects of twist and camber, fences, and horizontal-tail height on the static longitudinal stability of a 45 degree sweptback wing-fuselage combination of aspect ratio 8 at Mach number 0.19. Two different wings were investigated, one untwisted and one with twist and cambered. Results regarding wing-fuselage configuration and wing-fuselage configurations with horizontal tail are provided.

Report presenting an investigation to determine the overall performance of the three-stage turbine from the J71 turbojet engine. The turbine operated with a maximum brake internal efficiency of approximately 0.84 at an equivalent overall pressure ratio of approximately 3.6 and an equivalent rotor speed of about 110 percent of the equivalent design value.

Report presenting an investigation of a dynamic model to determine the effects of hull form, gross load, and aerodynamic trimming moments on the trim limits, trim, hydrodynamic moment, hydrodynamic resistance, total resistance, and rise of two streamline fuselages modified by chine strips. Results regarding effects of hull form and effects of gross load are provided.

Report presenting an investigation at subsonic speeds to determine the effects of lip shape and entrance Mach number on the characteristics of a scoop-type air-induction system designed for an airplane flying at supersonic speeds. Results regarding the ram-recovery ratio, static-pressure distribution, and drag are provided.

From Introduction: "The supersonic axial-flow compressor, for example, appears to offer advantages of high stage pressure ratio and height weight flows (reference 1) but problems peculiar to this compressor type have accompanied its introduction. For high single-stage pressure ratios (>4) the problem of converting the high dynamic energy to useful pressure arises (reference 2). In addition, the high tip speeds and weight flows combine to create a difficult situation for the turbine designer."

From Introduction: "The purpose of the investigation conducted at the NACA Lewis laboratory and reported herein was to determine the improvements possible in full-scale turbojet-engine performance when a single-annular combustor with slotted air-inlet orifices was used."

Report discussing an investigation of a delta-wing model with the leading edge swept back 60 degrees. Testing indicated that the gust load is greater than would be predicted by using a slope of the lift curve determined from steady-flow force tests. An aspect-ratio relation was determined for this type of wing with the selected apex angle, but it does not appear to be applicable to other wings with different apex angles.

"Ignition delay determinations of several fuels with nitric oxidants were made at simulated altitude conditions utilizing a small-scale rocket engine of approximately 50 pounds thrust. Included in the fuels were aniline, hydrazine hydrate, furfuryl alcohol, furfuryl mercaptan, turpentine, and mixtures of triethylamine with mixed xylidines and diallyaniline. Red fuming, white fuming, and anhydrous nitric acids were used with and without additives. A diallylaniline - triethylamine mixture and a red fuming nitric acid analyzing 3.5 percent water and 16 percent NO2 by weight was found to have a wide temperature-pressure ignition range, yielding average delays from 13 milliseconds at 110 degrees F to 55 milliseconds at -95 degrees F regardless of the initial ambient pressure that ranged from sea-level pressure altitude of 94,000 feet" (p. 1).

Performance of the compressor, combustor, and turbine operating as integral parts of the XJ34-WE-32 turbojet engine was determined in the Lewis altitude wind tunnel over a range of altitudes from 5000 to 55,000 feet and flight Mach numbers from 0.28 to 1.05. Data were obtained for each of four exhaust-nozzle areas and are presented in graphical and tabular form.

Memorandum presenting a supplementary investigation conducted in the 20-foot free-spinning tunnel to determine the effect of external stores and lateral center-of-gravity displacement upon the spin and spin-recovery characteristics of a 1/20-scale model of the McDonnell F2H-3 airplane. Results regarding the tests with wing-tip tanks installed and with the experimental aerodynamic shape installed are provided.

This report discusses what effects the shift of an orbital axis relative to the center of the table-top stellarator tube as well as the magnitude of these effects.

Discussing the importance to mapping of the Salt-Bluff contacts at King tut Mesa

Discussing recommendations for drilling parts of the Coal Creek Anticline in Rio Blanco County, Colorado

The results of a preliminary investigation to develop a nose shape suitable for housing an infrared seeker are presented. The zero-lift drag characteristics of a missile-like body with various unconventional nose shapes were obtained through a range of Mach numbers from 0.8 to 1.8 and Reynolds numbers, based on body length, from 20 x10 to the 6th power to 70 x 10 to the 6th power, respectively, by using rocket-propelled free-flight models. Results of the test indicate that at supersonic speeds about 70 percent of the drag penalty incurred by using spherical-tip nose shapes may be eliminated by using nose shapes which will still allow the seeker to function.

The geometry of the magnetic pole structure in the cloverleaf cyclotron suggests the use of three dees excited by three phase rf placed in the valleys out of the way of the beam. Experience with the model machines indicates that it is desirable to be able to vary the phase angles between the three dee voltages through 30 or 40 degrees and to be able to maintain them at any given value within plus or minus one degree. It is desirable, also, to be able to vary the phase angle independently of the amplitude of the dee voltages. There are several possible ways of meeting these requirements. The one which was chosen appears to be the most flexible and to best meet the problems presented by the center geometry of the machine.

This technical report presents necessary information required to operate the raw materials feed preparation plant. The information herein is intended to serve as a guide to operating personnel and to provide general data concerning the process.

Technical report focusing on the Homogeneous Reactor Experiment (HRE) construction, completed 60% as of August 15, 1951. Report also includes alternate systems studies and long range studies of the Homogeneous Reactor Experiment. Technical report is organized in three parts. [From Summary]

Uranium ore from Radium Hill, South Australia was leached with hot sulfuric acid solutions and the uranium recovered from solution by uranous phosphate precipitation or by use of anion exchange resins.