From Introduction: "The altitude performance characteristics of the prototype J40-WE-8 turbojet engine were determined in the NACA Lewis altitude wind tunnel. The altitude operational characteristics of the engine are presented herein. The results of a brief study of the effect of the two different grades of fuel (MIL-F-5624A grades JP-3 and JP-4) on steady-state engine performance at an altitude of 45,000 feet and a flight Mach number of 0.20 are also given."

The results of an analytical investigation of the theoretical air specific impulse performance and adiabatic combustion temperatures of several possible ram-jet fuels over a range of equivalence ratios, inlet-air temperatures, and combustion pressures, is presented herein. The fuels include octane-1, 50-percent-magnesium slurry, boron, pentaborane, diborane, hydrogen, carbon, and aluminum. Thermal effects from high combustion temperatures were found to effect considerably the combustion performance of all the fuels. An increase in combustion pressure was beneficial to air specific impulse at high combustion temperatures. The use of these theoretical data in engine operation and in the evaluation of experimental data is described.

This report deals with the (1.1) physical properties of graphite, (1.2) effects of pile irradiation on the properties of graphite, (1.3) effect of irradiation on "ceramic" materials, (1.4) exposure and dosage for radiation damage experiments, (1.5) apparatus for the measurement of the thermal conductivity of solids, (1.6) effects of radiation on ice -- the thermoluminescence of ice, (1.7) investigation of color centers and other optical properties of single crystals. (2.1) radiation chemistry of liquids, (3.1) radiochemical investigation of the spontaneous fission of Cm242, (3.2) radiochemical service, (3.3) on the one-body model of alpha, (4.1) spectrographic analysis, (4.2) chemical analysis, (5.1) the 60-inch cyclotron.

Unanticipated radioactive contamination of the 200 Areas environs was discovered in the latter part of 1947, about 2.5 years after the startup of the Bismuth Phosphate Separation Plants. It was subsequently established that this contamination was due to radioactive particles emanating from the Separation Plants' stacks, and the need for exhaust ventilation air filtration equipment was recognized. Sand filters were installed in the fall of 1948 in the ventilation systems of the B and T Bismuth Phosphate Plants. These filter units essentially eliminated this contamination problem and have performed satisfactorily to the present time.

Introduction: "In the early operation of the WTR severe canal corrosion of dummy fuel assemblies and a beryllium A-piece caused a great deal of concern as to the possible effects of long-time canal storage on such elements. A short-term experimental program was started to determine the causes of this corrosion and to correct them before any irradiated fuel elements had to be stored in the canal. The results of this program are presented here."

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Drag and longitudinal trim at low lift of the North American YF-100A airplane at Mach numbers from 0.76 to 1.77 as determined from the flight test of a 0.11-scale rocket model are presented herein. Also included are some longitudinal stability and some qualitative pitch-damping data.

Memorandum presenting an investigation conducted in the 4- by 4-foot supersonic pressure tunnel at Mach number 2.01 to determine the static stability and control characteristics of a canard-type missile configuration with large deflections of the canard controls and with deflection of wing-tip controls. The results of the investigation indicated that with a 30 degree deflection of the canard control a maximum trim normal-force coefficient of 0.4 and a maximum trim angle of attack of 12 degrees might be obtained for the optimum center-of-gravity location.

Report presenting an investigation in the 16-foot transonic tunnel to determine the effect of leading-edge chord-extensions on the aerodynamic characteristics of a sweptback wing-fuselage combination at several Mach numbers. Results regarding the effect of chord-extensions on longitudinal stability for wing-normal configuration, effect of chord extensions on lift for wing-normal configurations, effect of chord-extensions on drag and lift-drag ratios of wing-normal configurations, effect of chordwise fences on the aerodynamic characteristics of a wing-normal configuration, and effect of chord-extensions on the pitching moment and lift characteristics of a wing-art configuration are provided.

Report presenting an experimental investigation using a 1 7/8-inch diameter burner to determine the effects of particle size and stabilizing additives on the combustion performance of magnesium-hydrocarbon slurry fuels. Results regarding an evaluation of the sampling method, blow-out velocity, and combustion efficiency are provided.

Corrosion rates of present reactor grade uranium were measured in boiling distilled water and were found to have higher values almost by a factor of two then previously reported corrosion rates of uranium. Mallinckrodt biscuit metal showed corrosion rates in the same medium somewhat lower than reactor grade uranium, and high purity metal prepared at Argonne National Laboratory corroded considerably less rapidly than the biscuit metal.

Report presenting testing of the effectiveness of transpiration cooling of an 8 degree total angle conical body with water removed onto the surface through a porous section near the nose. Results regarding a reference test without cooling, a cooling test with 0.010 pound of water per second, a cooling test with 0.0025 pound of water per second, a hypothesis of the phenomena of liquid transpiration cooling, water consumption are provided.

Report presenting cold-flow free-flight tests at zero lift to investigate the possibility of flutter of simulated wing-ram-jet-nacelle configurations which were 1/9-scale models of the wing and ramjet nacelles of the Grumman XSSM-N-6a missile. Testing was performed on three different configurations. Results regarding Mach number, velocity, aerodynamic density, and flutter are provided.

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Many procedures for the chemical isolation of the microscopic angular inclusions in rolled uranium have been investigated. Four were selected as most satisfactory for this work and will be described in detail. The procedures are: (1) the copper displacement of the uranium, (2) the electrolytic displacement of the uranium, (3) the chemical dissolution of the uranium in an anhydrous solution of hydrogen chloride in methanol, and (4) the chemical dissolution of the uranium in an aqueous solution of hydrogen chloride and hydrogen peroxide.

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Abstract: "The information contained in this report consists of personnel exposures to radioactive dust resulting from a thorium rolling operation."

Report presenting an investigation in the transonic tunnel to determine the influence of a change in body shape on the effects of twist and camber. Twist and camber were found to greatly improve the maximum lift-drag ratios of the wing-modified fuselage configuration through the speed range, but reduced the ratios for a wing-curved fuselage configuration. Results regarding basic aerodynamic data are also provided.

Report presenting an investigation conducted with several 73-percent semispan inboard spoiler ailerons, projecting 4 percent of the local wing chord from the wing surface, and located at the 70-percent chord line of a 45 degree sweptback wing-fuselage combination. Results regarding the effect of upper-surface spoilers on basic model characteristics, effect of gap on spoiler characteristics, comparison of upper- and lower-surface spoiler characteristics, comparison of upper-surface spoiler with oppositely deflected spoilers, effect of Mach number on spoiler effectiveness, and a comparison of spoiler effectiveness with aileron effectiveness are provided.

Report presenting an investigation of the feasibility of modifying the transient portion of the stick force in abrupt maneuvers in order to eliminate inadvertent normal-acceleration overshoots. The modification consists of additional stick force proportional to a quantity which leads the normal acceleration. The characteristics introduced by the inclusion of the force were considered to be very desirable by pilots.

Report presenting an investigation of a constant-area, circular 90 degree elbow of mean radius of curvature equal to its diameter with several arrangements of simple, nontwisted, rectangular vortex generators. The inlet flow had a boundary layer of about one-tenth the duct diameter. Results regarding an elbow with no vortex generators and an elbow with vortex generators are provided.

Report presenting an investigation to determine the lateral control characteristics of constant-percent-chord trailing-edge elevons on a tailless wing-body combination with a pointed wing of aspect ratio 2. The effectiveness of inset tabs in reducing the elevon hinge moment was also determined. Results include the lift, drag, pitching moment, rolling moment, elevon hinge moment, tab moment, elevon load, and center of pressure of elevon load.

Results are presented, in graphical and tabular form, from a wind tunnel investigation of the lift, drag, and pitching moment characteristics of thin, low-aspect-ratio wings in combination with a body at Mach numbers from 0.25 to as high as 1.9. The following are analyzed and compared with existing theoretical results: 1. Effects of aspect ratio on 3-percent-thick triangular wings; 2. Effects of plan form on 3-percent-thick triangular, sweptback, and unswept wings of aspect ratios 2 and 3; 3. Effects of wing thickness on triangular wings of aspect ratio 2; 4. Effects of profile shape on triangular, sweptback, and unswept wings; and 5. Effects of camber and twist on triangular wings of aspect ratios 2 and 4.

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