Report presenting an investigation studying the effects of compressibility on the internal-flow characteristics of an NACA 1-series cowling-spinner combination equipped with a dual-rotation propeller at Mach numbers up to 0.8. Two propellers were examined, one with a sealed propeller-spinner juncture and one with a raised-platform-airfoil shaped juncture. The propeller was not found to have appreciable compressibility effects on the impact pressures when operating at design cruise blade angle.

Report presenting testing of the transonic longitudinal characteristics of a model of the McDonnell XF3H-1 airplane. The model had a center-of-gravity location of 28.5 percent of the mean aerodynamic chord and a stabilizer setting of -5.91 degrees relative to the wing chord plane with extensible rocket racks. Results regarding Reynolds number, rocket-rack program, flight time history, trim, lift, drag, longitudinal stability, directional stability, and inlet pressure recovery are provided.

Memorandum presenting the results of a test on the transonic longitudinal characteristics of a scale rocket model of the McDonnell XF3H-1 airplane. The model, flown with a center-of-gravity location of 28.5 percent of the mean aerodynamic chord and a stabilizer setting of -5.91 degrees relative to the wing chord plane, was equipped with extensible rocket racks. Results regarding the Reynolds number, rocket-rack program, flight time history, trim, lift, drag, longitudinal stability, directional stability, and inlet pressure recovery are provided.

Report presenting an investigation to evaluate the effects of nacelles and extended split flaps on the longitudinal characteristics of a wing-fuselage-tail combination of a type believed to be suitable for long-range high-speed airplanes. Wind tunnel tests to study the effects of the nacelles and flaps were conducted at a range of Mach and Reynolds numbers. Results regarding the effects of the nacelles with the tail off, effects of tail height, effects of nacelles with the tail on, and effects of flaps are provided.

Report presenting an investigation to determine the effect of rate of flap deflection on flap hinge moment and wing lift at a range of Mach and Reynolds numbers. For the rate of flap-deflection range investigated, the hinge-moment coefficient was practically independent of rate of flap deflection.

Report presenting an investigation of systematic series of sharp- and blunt-trailing-edge wings to determine the effects of thickening the trailing edges on the lift, drag, and pitching moment characteristics at several Mach numbers. Results indicate that no appreciable zero-lift drag reduction can be obtained by thickening the trailing edges from 1.41 to 1.96, but trailing edges can be thickened appreciably with no increases in zero-lift drag.

The elastic differential scattering cross section of 190 MeV deuterons by protons has been measured from 15 degrees to 170 degrees in the center of mass system. The cross sections were obtained by subtracting the carbon counts from those received with a polyethylene target. Part I presents a description of the experiments. Results are shown in Table IV and Fig. 3. Part II compares these results with those expected from theory by making use of a method developed by Chew. A summary of this comparison is given in Table VII.

The results of electrical resistance measurements have been used as a means of following changes occurring in metals due to irradiation. The electrical conductivity is sensitive to changes in composition and to cold-work or structure damage. In an anisotropic metal, such as uranium, the director of measurement also influences to some extent the values obtained. For these reasons it is essential to use the same material, and if possible the same piece of material, in comparing the electrical properties before and after irradiation. This report is a description of the measurements made on pieces of the same uranium rod before and after an exposure of approximately 150 MWD/T. The results, while preliminary in nature and dealing only with one sample and exposure level, provide data for which a comparison may be made of the electrical resistivity of irradiated and non-irradiated uranium metal.

Statistical methods were employed to measure relative values of electron loading and spark-over voltage for a large number of unoutgassed electrode materials. Test voltages up to 110 KV were employed in vacuum of the order of 10<sup>-7 mm Hg. All metals showed a square root dependence between spark-over voltage and spacing.

Our hypothetical Trustee recognizes that the economic and social pressures directed at finding new sources of abundant low-cost energy are about to become compelling. As a prudent Trustee, he would say the time for action has come. He would urge that the nation's talents, public and private, be released for the development of nuclear furnaces (reactors) capable of furnishing heat for the generation of electricity, for district central heating and for industrial process heating. He would urge that we continue to explore nuclear reactions other than the fission of uranium and thorium. There is hope of domesticating the fusion reaction that makes the hydrogen bomb go. Economical fusion of the hydrogen contained in a cubic mile of sea water would be a source of capital energy equal to all conceivable needs for many hundreds of years. He would be concerned about the vast quantities of metals, some of them already in short supply, that would be required by very large nuclear power programs. He would suggest that we search for these metals by methods yet to be developed, and in novel places, including the sea. Finally, as our ultimate anchor to windward, he would urge the exploration of all ways …

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Report presenting an experimental investigation using a 1 7/8-inch diameter burner to determine the suitability of residual fuel oils as carriers in magnesium slurries. Four residual fuel oils with varying viscosities were investigated by themselves and in slurries of 50 percent magnesium. Results regarding the settling characteristics, blow-out velocity, and combustion efficiency are provided.

Report presenting studies of some of the effects of parameters such as Mach number, blade angle, and structural damping on the flutter of model helicopter rotor blades in the hovering condition. Forward movement of the blade chordwise center-of-gravity location tended to raise the flutter speeds at low pitch angles, but had no effect at high pitch angles. The significant flutter data for the tests along with detailed descriptions of the models are included to facilitate more detailed analyses.

Report presenting free-flight measurements of the zero-lift drag of a cruciform-finned body at a range of Mach and Reynolds numbers. Results regarding experimental total drag, comparison of theory with experiment, comparison of experiment with NOL results, boundary-layer transition, Reynolds number effects, and fin leading-edge shape are provided.

Report presenting information on landing gear applied drag loads and the nature of wheel spin-up in landing based on testing in the Langley impact basin. Particular attention is paid to the nature and variation of the coefficient of friction between the tire and runway during the wheel spin-up process. Results regarding the fundamentals of the process, comparison of maximum loads, variation of coefficient of friction, and effect of prerotation are provided.

"Aeroelastic instability phenomena of isolated open and closed rigid bodies of revolution free to move under elastic restraint have been investigated experimentally at low speeds by means of models suspended at zero angles of attack and yaw on slender flexible struts from a wind tunnel ceiling. Three types of instability were observed - flutter similar to classical bending-torsion flutter, divergence, and an uncoupled oscillatory instability which consists in nonviolent continuous or intermittent small-amplitude oscillations involving only angular deformations. The speeds at which this oscillatory instability starts were found to be as low as about one-third of the speed at flutter or divergence and to depend on the shape of the body, particularly that of the afterbody, and on the relative location of the elastic axis" (p. 1).

Report discussing a study conducted to test carbonaceous materials and other substances ability to remove uranium from aqueous solution. This study was based on the natural association of uranium and carbonaceous.

Information on experimental facilities and reactors.

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The general program established at Argonne National Laboratory in connection with the Fast Power Breeder Reactor (P BR) includes performance of exponential experiments on assemblies having compositions which may exist in the reactor core. This report deals with that phase of the program known as the Fast Exponential Experiment which may be described very briefly as follows: An assembly of fissile U/sup 235/ and fertile material (too small to be self- critical) intermixed with poisons (such as are encountered in the mechanical structure and coolant system of a self-sustaining reactor) is fed with neutr ons from an auxiliary source. By measurements of the neutron flux within the assembly, important parameters can be calculated which are necessary to the proper design of an actual critical reactor of the same composition. (auth)

The general program established at Argonne National Laboratory in connection with the Fast Power Breeder Reactor (PBR) includes performance of exponential experiments on assemblies having compositions which may exist in the reactor core. This report deals with that phase of the program known as the Fast Exponential Experiment which may be described very briefly as follows. An assembly of fissile (U-235) and fertile material (too small to be self-critical) intermixed with poisons (such as are encountered in the mechanical structure and coolant system of a self-sustaining reactor) is fed with neutrons from an auxiliary source. By measurements of the neutron flux within the assembly, important parameters can be calculated which are necessary to the proport design of an actual critical reactor of the same composition.

Pile temperature control is normally maintained by using four horizontal rods, two ``long`` rods extending to the far side of the pile and two ``short`` rods whose tips are on the near side. (1) This procedure prevents cycling of ``hot spots`` about the pile, but does not achieve symmetrical horizontal temperature distribution. Prior to pile operation the cadmium-containing cans were removed from the near ends of the two ``long`` control rods, numbers 5 and 11, at C pile, so that when these rods were in the ``full in`` position their poisoning effect outside the flattened region at the near side of the pile would be small. By using these ``half rods`` in conjunction with ``short`` rods it was expected that a nearly symmetrical horizontal temperature distribution could be maintained. A comparison of near-to- far temperature distribution at C-pile with other piles indicates that gains in production of 4% during early operation of a pile and 3% during later equilibrium operation can be realized by using the half-rods. On the basis of these observations ``half-rods`` are to be incorporated in the K-piles currently under construction. It is recommended that the ``long`` control rods in existing piles be replaced by rods altered …

Report presenting measurements of chordwise pressure distributions at four spanwise stations over a 10-percent-thick wing of the Bell X-1 airplane. Results regarding pressure distributions at the various stations and section aerodynamic characteristics are presented. The data was obtained for a range of Mach numbers from 0.30 to 11.9 and altitudes from 17,000 to 47,000 with several different types of maneuvers.

Report presenting a flight investigation on a four-engine bomber airplane to determine the effects of wing flexibility on wing strains developed in flight through clear-air turbulence. Amplification of the effects appeared to be a function of gust-gradient distance and was not significantly affected by airspeed or weight.