Introduction: In anticipation of the design of equipment for heat transfer tests, a series of short exposure corrosion tests was initiated in an effort to determine the order of magnitude of the corrosion involved. Information was required on the effect on corrosion rates of applying a potential between two concentric tubes, the annulus between them containing condensate water.

From introduction: During the summer of 1951, Navajos conducted John W. Chester, Russell C. Cutter, and E. V. Reinhardt, Grand Junction Exploration Branch, U. S. Atomic Energy Commission, to a copper deposit in Copper Canyon. Little radioactivity was noted, and no further work was done in the area at that time. In October 1951, the same group of Navajos reported the discovery of uranium ore in another portion of the same area. The site was visited by Cutter who noted that an excavation made by the Navajos had disclosed a 3-foot thickness of low-grade uranium ore. In November 1951, Cutter again visited the area and observed that the Navajos had opened a 5-foot face of good ore.

From introduction: This report details the results of the post-irradiation examination of a test involving one defected rod and one undefected rod.

Memorandum presenting the performance of a scoop-type inlet on the bottom of a body of revolution at several Mach numbers and angles of attack. The investigation included a study of the effects of altering the approach surface ahead of the inlet, extending the boundary-layer splitter plate, and bleeding air at the throat and exit of the diffuser.

Report discussing an investigation to determine the drag of a configuration with a body of fitness ratio 12 with stabilizing tail surfaces and a 12-percent-thick 30-degree swept-forward wing using the free-fall method. The drag oft he wing and the total drag were measured separately and compared. The swept-forward wing was found to greatly increase the effect of drag on the body-tail combination.

Memorandum presenting pressure-distribution and force data at various angles of attack of a triangular wing of aspect ratio 2 and having an NACA 0005 modified section. The wing had a plain, constant-chord, trailing-edge flap which was deflected 0 and 10 degrees. Results regarding the gross force characteristics of the wing, including lift, drag, pitching-moment, and flap hinge-moment coefficients are provided.

Report presenting a theoretical investigation of the lateral stability of a towed high-speed fighter plane using a fighter cruising at supersonic speed at 50,000 feet and a 1000-foot cable. The motion of this configuration was shown to have highly unstable oscillation caused by the towline restraint, but the configuration can be stabilized by choosing the right position for the towline connection and several types of automatic controls.

The results of transonic flight measurements of the longitudinal stability characteristics of the Douglas D-558-II research airplane in the original configuration and with outboard fences mounted on the wings are presented. The levels of normal-force coefficient at which the stability decreases and pitch-up starts have been determined for both airplane configurations at Mach numbers up to about 0.94.

From Summary: "A sturdy stiffener is defined as a stiffener of such proportions that it does not suffer cross-sectional distortion when moments are applied to some part of the cross section. When such a stiffener is attached to one edge of a plate, it will resist rotation of that edge of the plate by means of its torsional properties. A formula is given for the restraint coefficient provided the plate by such a stiffener. This coefficient is required for the calculation of the critical compressive stress of the plate."

The use of a magnetic field to control the motion of electrically conducting fluids is studied. The incompressible boundary-layer solutions are found for flow over a flat plate when the magnetic field is fixed relative to the plate or to the fluid. The equations are integrated numerically for the effect of the transverse magnetic field on the velocity and temperature profiles, and hence, the skin friction and rate of heat transfer. It is concluded that the skin friction and the heat-transfer rate are reduced when the transverse magnetic field is fixed relative to the plate and increased when fixed relative to the fluid. The total drag is increased in all of the areas.

Report presenting an investigation of the performance of pentaborane fuel in a flight-type, 9.75-inch-diameter ramjet engine mounted in a connected-pipe altitude facility. Combustor efficiency was above 85 percent throughout the range of test conditions. Results regarding the connected-pipe performance and estimated flight performance are provided.

Report discussing the distribution of mass in the spontaneous fission of Cm²⁴², which was investigated by a radiochemical determination of the fission yields of twenty-one nuclides ranging in mass from 91 to 140. "Corrections for absorption, scattering, geometry, decay, and fractional saturation were applied to obtain saturation disintegration rates, which, with the known fission rate of the source, give the fission yields."

Report discussing a procedure for the preparation of anhydrous vanadium trifluoride. From abstract: "By selecting proper operating conditions and equipment, a method of preparation was devised such that anhydrous vanadium trifluoride of high purity was produced reliably in five pound batches." The method of preparation involves manipulating the starting material, vanadium pentoxide.

Abstract: "This paper gives an arithmetic method of computing the number of sections required in a catalytic tower to produce a given enrichment. It also tells how to calculate the enrichment of a tower with a given number of sections. The problem of the most economical design of catalytic towers is solved. Methods are given for determining the temperature, the efficiencies of catalyst beds and strippers, the relative production rate, and the water vapor-hydrogen gas ratio which give the optimum combination of operating pressure, cross sectional area, number of sections, and volume of catalyst in the tower. Simple directions as to how to make the calculations are included."

Report discussing the progress made on the Experimental Breeder Project during the period from March 1, 1949 to January 31, 1950.

This report will summarize what has been done and present the interpretations made at this stage of the program.

This report summarizes experimental results obtained for the General Electric Company under terms of Design, Development and Research Contrast DDR-33. A discussion of the results, the manner in which they were obtained and their probable accuracy are included. Suggested improvements or modifications of properties of this nature be contemplated.

A complete investigation was made of the r-f field in the 1/10-scale Materials Testing Accelerator (Mark I) cavity

Memorandum presenting a study of the performance of a scoop-type inlet on the bottom of a body of revolution at a range of Mach numbers and angles of attack to 10 degrees. The investigation included a study of the effects of altering the approach surface ahead of the inlet, extending the boundary-layer splitter plate, and bleeding air at the throat and exit of the diffuser. Results regarding the flow survey ahead of the inlet, alternative configurations, internal-flow details of the basic configuration, air bleed at the throat, and air bypass at the engine face are provided.

Report presenting a flight investigation to determine the static-pressure errors for nose-boom airspeed installations of 17 airplanes. Both research-type and service-type aircraft are covered in the investigation. Results indicated that the magnitude of static-pressure errors for the airspeed installations of all the airplanes is shown to vary with airplane geometric characteristics that include nose-boom length, fuselage diameter, and nose fineness ratio.

Report presenting testing of several underslung scoop-type inlets mounted on a body of revolution at several Mach numbers through a range of angles of attack. Geometric differences between inlets included ramp angle, frontal area, splitter-plate height, and aspect ratio. Results regarding inlet stability, peak pressure recoveries, and total-pressure distortions are provided.

"An investigation was made in the Langley 300 MPH 7- by 10-foot tunnel to determine the aerodynamic characteristics of three deep-stepped planing-tail flying-boat hulls differing only in the amount of step fairing. The hulls were derived by increasing the unfaired step depth of a planing-tail hull of a previous aerodynamic investigation to a depth about 92 percent of the hull beam. Tests were also made on a transverse-stepped hull with an extended afterbody for the purpose of comparison and in order to extend and verify the results of a previous investigation" (p. 1).

This report gives a complete description of the full-scale wind tunnel of the National Advisory Committee for Aeronautics.

As a part of this investigation, the acceleration characteristics of the engine, using the standard engine fuel-control system, were obtained for conditions simulating flight at altitudes of 35,000 and 50,000 feet with a flight Mach number of 0.4. Rapid and wave-off type accelerations were made at each flight condition, and the transient performance of the engine was recorded with a multiple-channel oscillograph. The parameters are presented graphically in the form of time histories, augmented by short segments of the oscillograph recordings, in order to more completely describe the behavior of the engine parameters when surge was encountered.