Abstract: "The mechanical properties of a large number of zirconium alloys have been investigated. These alloys include zirconium-tin and zirconium-tin-uranium. Tensile tests have been run on these alloys at room temperature, 500 F, and 600 F. Hot-hardness data have been obtained from room temperature to 1600 F, with particular emphasis on the hot-rolling range. Creep tests and fatigue tests have been run on a number of zirconium-tin alloys at 500 F."

Abstract: "The mechanical properties of a large number of zirconium alloys have been investigated. These alloys include zirconium-tin and zirconium-tin-uranium. Tensile tests have been run on these alloys at room temperature, 500 F, and 600 F. Hot-hardness data have been obtained from room temperature to 1600 F, with particular emphasis on the hot-rolling range. Creep tests and fatigue tests have been run on a number of zirconium-tin alloys at 500 F."

This report explores the production of beta silicon carbide, a low-temperature, cubic modification of cubic silicon carbide. The temperature, heating time, type of starting material, and proportion of starting materials were all varied in order to test yields of beta silicon carbide.

From to the files: The Shinarump-Moenkopi contact on Oljetoh Mesa in the Monument Valley district, Arizona-Utah, was examined from November 5 to 15, 1951, to determine the location of and the mineralization in Shinarump channels. Twenty-seven distinct channel outcrops were located and examined. Three of these channel outcrops are mineralized and the remaining 24 are barren. Plate I shows the distribution of the Shinarump, the Moenkopi, and the DeChelly member of the Cutler formation; the location of the Shinarmp channel outcrops; the channel trend where there is good evidence for such a trend. The Hoskinrnini tongue of the Cutler was mapped with the Moenkopi as it is not a good mappable unit in this area. The three mineralized outcrops are indicated by the letters A, G, and AA while the barren outcrops bear the letters B to F and H to Z.

From introduction: The purpose of an airborne radioactivity survey is to locate ground areas of higher than normal radioactivity which might lead to discovery of uranium mineralization. For this type of survey, gamma-ray detection equipment employing either a geiger counter or a scintillation counter can be mounted in a fixed wing aircraft or a helicopter.

Report presenting the specific impulse, characteristic velocity, thrust coefficient, and heat rejection of liquid fluorine and a fuel consisting of a hydrazine-ammonia mixture for a range of fuel percentages in a 100-pound-thrust rocket engine designed for a combustion-chamber pressure of 300 pounds per square inch absolute. The fuel consisted of 59 percent hydrazine, 37 percent ammonia, and 4 percent water. The attainment of maximum performance with liquid fluorine as a rocket oxidant will require a critical study of injector design.

Report presenting an investigation of the effect of fuselage-mounted rocket boosters on a strut-mounted engine in the 8- by 6-foot supersonic wind tunnel at Mach numbers of 1.8 and 2.0. The boosters were pairs of circular cylinders with conical forebodies mounted on the top and bottom of the fuselage, and the engine was mounted on a horizontal strut. Results regarding the characteristics of the flow field, effect of putting the boosters in several positions, and effect of angle of attack are provided.

Report presenting an investigation for stationary turbine blades with 10 tubes and 13 fins forming the internal heat-transfer surfaces in order to accurately predict local turbine blade temperatures. Results regarding the comparison of calculated and measured midchord blade temperatures, comparison of calculated and measured temperatures near blade trailing edge, comparison of calculated and measured temperatures near the blade leading edge, the influence of errors in calculated temperatures on design considerations, and an application of the analysis to other blade configurations are provided.

Report presenting measurements in free fall at transonic speeds of the dynamic stability characteristics of three models. Two of the models had 45 degree swept wings of aspect ratio 6 and 45 degree swept tail surfaces and differed only in that one had plane wings and one was cambered and twisted. The third had the same fuselage-tail arrangement but no wing.

Report presenting the performance characteristics of one convergent and three convergent-divergent nozzles obtained over a range of nozzle pressure ratios. Results regarding one-dimensional flow theory and the performance characteristics themselves are provided.

Report presenting a study of the altitude-starting limits of a production turbojet engine with an axial-flow compressor and a multiple through-flow combustor. The ignition limits, flame-propagation limits, and acceleration limits of the engine were improved to increase the starting limits to relatively high altitude.

Report of an investigation of the overall performance characteristics of a complete missile configuration in the 8- by 6-foot supersonic wind tunnel at several Mach numbers, angles of attack, canard-control-surface deflections, and a designated Reynolds number based on wing mean aerodynamic chord. The investigation showed that at a Mach number of 2.0, the addition of engines to a no-engine configuration increased drag and moved the aerodynamic center rearward but produced little additional lift. Results regarding force and moment evaluation and engine-internal-flow evaluation are provided.

The performance characteristics of a downward canted normal-shock side (scoop) inlet located downstream of a triangular control surface are presented for free-stream Mach numbers of 1.5 and 1.8 in terms of total pressure recovery and mass flow ratio for various boundary-layer removal systems, angles of attack, control surface deflections and adverse yaw. An engine operating condition for a hypothetical turbojet engine is established, and the match point characteristics of the engine-inlet configuration are summarized. It is shown that the diffuser performance increases with increased boundary-layer removal and decreases because of the presence of the wake from the forward control surface.

Report presenting an investigation of liquid-film cooling at a variety of air temperatures and Reynolds numbers. Results regarding the effect of coolant flow per circumferential length on liquid-cooled length, correlation of heat transfer from hot gas to liquid film for constant coolant flow per circumferential length, and generalized plot of film-cooling data based on heat-transfer correlation at constant coolant flow per circumferential length are provided.

Report presenting experimental force and moment data obtained by pressure measurements on a wing of aspect ratio 8.02, 45 degree sweepback of the quarter-chord line, taper ratio of 0.45, and NACA 63(sub 1)A012 airfoil sections, which are compared with the calculated loadings obtained by standard methods and several variations of the methods. Results regarding the system of identifying solutions, spanwise load distribution, lift-curve slope, center of pressure, wing pitching moment, and induced drag are provided.

Report presenting an investigation to determine the effect of varying the span and deflection angle of a 15-percent-chord slat on the longitudinal aerodynamic characteristics of a semispan wing with 49.1 degrees of sweepback at the leading edge, an aspect ratio of 3.78, a taper ratio of 0.586, and NACA 65A006 airfoil sections. Force measurements and chordwise pressure distributions were obtained on the wing and extended slat with and without a deflected trailing-edge flap.

"Wake development behind circular cylinders at Reynolds numbers from 40 to 10,000 was investigated in a low-speed wind tunnel. Standard hot-wire techniques were used to study the velocity fluctuations. The Reynolds number range of periodic vortex shedding is divided into two distinct subranges" (p. 1).

Abstract: The experimentally determined exponential dependence of spontaneous fission rate on Z^2/A has been used to derive an expression for the dependence of the fission activation energy on Z^2/A. This expression has been used to calculate the activation energy for slow neutron induced fission and photofission. The correlation with the experimental data on these types of fission seems to be quite good.

Report discussing the refractory properties of pure uranium dioxide, as well as methods for forming the compound. Health hazards of uranium dioxide are briefly mentioned.

Quarterly report which includes brief summaries of research studies related to technology materials and accelerator testing.

The analysis shows that a symmetrical three-dee cyclotron accelerating ions below relativistic velocities has the property that ions of different e/m rations can be accelerated without changing the frequency of the electrical power supplied to the dees or the value of the magnetic field. The energy gain per revolution of the ions which can be accelerated in the various modes are found, considering three identical dees of arbitrary angular widths. For these calculations it has been assumed that a step-function voltage change occurs at each edge of the dees.

From introduction: "This report covers work performed in the Solid State Division for the quarter ending May 10, 1952." Topics covered include radiation metallurgy, engineering properties, solid state reactions, crystal physics, and special projects.

Report presenting the lateral-control characteristics of two spans of spoiler and flap-type ailerons on an unswept wing with an aspect ratio of 2.5 and hexagonal airfoil sections. Measurements of rolling moments, yawing moments, aileron hinge moments, normal forces, and balance-camber pressures for various configurations of the wing.

"The applicability of some results from the theory of generalized harmonic analysis (or power-spectral analysis) to the analysis of gust loads on airplanes in continuous rough air is examined. The general relations for linear systems between power spectrums of a random input disturbance and an output response are used to relate the spectrum of airplane load in rough air to the spectrum of atmospheric gust velocity. The power spectrum of loads is shown to provide a measure of the load intensity in terms of the standard deviation (root mean square) of the load distribution for an airplane in flight through continuous rough air" (p. 371).