Investigation conducted to determine the cause of cracking, during tension, on the surface of tensile specimens of uranium-molybdenum alloys.

"Abstract: The advantages of storing nuclear pulse height information on tape for later use with an analyzer are pointed out. Experiments with a magnetic modulator playback head which would offset inaccuracies due to tape speed variation are described. (T.R.H.)."

From introduction: "The tube arrangement covered in this report was proposed in June, 1950, as a means of halving the weight and volume required for the heat exchanger. Ideally, the pressure drop across this arrangement should be little more than that required to overcome the skin friction on the tube surfaces. If the pressure drop across the tube spacers and in the cross-flow regions can be kept low, this ideal can be approached. much of the test work covered in this report was devoted to this phase of the problem."

The following report provides results from investigations on the operation of the power supply for the Bevatron Magnet as well as maintenance problems.

Report describing the effects of pile irradiation on fuel materials and coil springs for the Submarine Intermediate Reactor. The investigation was called for by Hanford Irradiation Request No. 79. Results of investigation are detailed in the report.

Memorandum presenting an investigation in natural icing conditions to determine the effect of ice formations on the performance of an axial-flow turbojet engine. A description of the change over time in tail-pipe temperature, engine jet thrust, fuel flow, ice collection, and acceleration qualities are provided.

Investigation at transonic speeds in the high-speed 7- by 10-foot tunnel to determine the rolling-effectiveness characteristics of a spoiler on a double-wedge-type semispan wing with a sweepback angle of 42 degrees. Results regarding the variation of rolling-moment coefficient, spoiler effectiveness, and rolling effectiveness are provided.

Report presenting the results of flight tests showing lateral oscillation in the Bell X-1 and calculations created to determine the effects of changes in several mass and aerodynamic parameters on the lateral oscillations. Calculations indicate that lateral stability should be improved by a more positive inclination of the principal axis of inertia or a reduction of the value of yawing moment of inertia.

Memorandum presenting measurements made in the transonic speed ranges of the static-pressure position error at a distance of 0.96 chord ahead of the wing tip of both the 8-percent-thick-wing and the 10-percent-thick-wing X-1 airplanes, and at a point 0.6 maximum fuselage diameter ahead of the fuselage nose of the X-1 airplanes. Results regarding the accuracy of pitot-static heads, static-pressure error of wing-tip installation, static-pressure error of the fuselage-nose installation, and error in total pressure are provided.

Memorandum presenting a description of an axial-discharge mixed-flow compressor, which is especially adapted for jet engines because of the large mass flow per unit frontal area. The best impeller was selected on the basis of the maximum air-flow capacity, which was 19.6 pounds per second for a 14-inch-diameter impeller with a tip speed of 1480 feet per second and a pressure ratio of 3.5.

Report presenting an analysis of an axial-discharge mixed-flow compressor designed to combine the compactness, reliability, and wide operating range of a mixed-flow compressor with the high flow capacity per unit of frontal area that characterizes the axial-flow compressor. The primary objective of this design was to maximize the flow capacity for a predetermined pressure ratio. Results regarding the flow distribution at the impeller inlet, flow distribution at the impeller outlet, and impeller performance are provided.

Report discussing an investigation of the longitudinal stability, trim, and drag of a rocket-propelled model at low lift coefficients at a range of Mach numbers. the configuration included a wing and horizontal tail of aspect ratio 4 and thickness ratio in the streamwise direction of 6 percent.

Report presenting a preliminary investigation of a wedge-type compression surface mounted vertically in a circular cowling conducted in the supersonic wind tunnel at a Mach number of 1.90 and range of angles of attack. With symmetrical cowling, the pressure recovery and stability characteristics comparable to a conical inlet were obtained, but twin-duct flow interaction was observed. Results regarding the pressure recovery and stability characteristics and effects of removing the lower cowl lip and perforating the wedge centerbody are provided.

Report presenting an investigation of the effects of the wake resulting from control-surface deflection on the internal performance of two supersonic diffusers and on the engine-body interference drag in the 8- by 6-foot supersonic wind tunnel at Mach number 2.0. Results regarding the internal-flow evaluation, high-pressure-recovery diffuser, and drag evaluation are provided.

Data on the crystal structures of the common modifications of the elements at zero pressure.

Report discussing a study with the following objectives: "to synthesize pure specimens of both methylisoproplydiketone and 1,1 dinitroisobutane, to determine their physical and chemical properties, and to devise analytical methods which permit their quantitative determination in hexone-nitric acid systems to be encountered in the Redox Process."

A reinforced Butler building was exposed to fallout from Shots Diablo and Shasta, and the resulting dose rates and fallout deposition inside and outside the structure were measured with various instruments and techniques. Protection factors and roof and ground contributions to the total dose rates at points within the structure were determined from the measurements. Comparisons were made with the results of theoretical and other experimental studies. Information obtained from this experiment should be of value as basic experimental data for fallout protection work, although it is recommended that additional substantive data obtained under more controlled conditions.

Some data on the temperature effect in pulse columns are reviewed. New data obtained with the "vibrational" stirrer are reported. The effects on both the dispersion and coalescence and the net rate of extraction suggest that improved operation of the RA column and lowered waste losses would be expected at elevated temperatures.

Report issued by the Oak Ridge National Laboratory discussing the aging characteristics of the alloy Hastelloy B. Materials, equipment, experimental procedures, and results used to determine the characteristics of the alloy are presented. This report includes tables, illustrations, and photographs.

Report discussing the "equilibrium uranium distribution between an aqueous nitric acid solution and a 30 per cent by volume solution of tributyl phosphate in a hydrocarbon diluent" (p. 2). This includes the necessary equations.

An investigation was conducted to determine the effect of a coolant solution of 25 percent ethyl alcohol, 25 percent methyl alcohol, and 50 percent water by volume and maximum-economy spark advance on knock-limited performance and fuel economy of a large air-cooled cylinder. The knock-limited performance of the cylinder at engine speeds of 2100 and 2500 rpm was determined for coolant-fuel ratios of 0.0, 0.2, and 0.4. The effect of water-alcohol injection on fuel economy was determined in constant charge-air flow tests. The tests were conducted at a spark advance of 20 deg B.T.C. and maximum-economy spark advance.

Report presenting a survey and discussion of well-known microwave impedance measurement techniques. The discussion includes an introduction which emphasizes basic concepts and reflection coefficient-voltage standing-wave ratio relationships. Sources of error in the various measurement techniques are discussed and methods to reduce errors are presented. Methods using rotating loops and resonance lines are included and a brief discussion of microwave impedance standards is given.

A supplementary investigation on the stabilization of the Jettisonable nose section of the X-2 airplane has been conducted in the Langley 20-foot free-spinning tunnel. It was found that the nose section could be stabilized by the addition of curved fins which could be folded against the fuselage for normal flight.

Memorandum presenting a determination of the effect of nose shape on the normal-force, pitching-moment, and axial-force coefficients of a body of revolution with a fineness ratio of 10.94 as determined at subsonic speeds. Six nose shapes were investigated, which included flat-faced noses with various corner radii, a hemispherical nose, and two ogival noses.