The following report follows a test with the purpose of determining the effect upon image fidelity by exposing a television camera to high intensity radiation over an extended period. Provided later in the report are notes on the design of the utiliscope camera used for these tests due to notable design features.

Memorandum presenting the low-speed lateral control characteristics of a 32 degree sweptforward wing of aspect ratio 5.8 and NACA 65-series airfoil sections as determined in the 19-foot pressure tunnel. The investigation include the measurement of the hinge-moment and normal-force characteristics of an aileron and the rolling-effectiveness characteristics of the aileron and several configurations of spoilers.

Report presenting a low-speed investigation in the stability tunnel to determine the static longitudinal stability and control characteristics of two wing-fuselage combinations equipped with wing-tip controls of half-diamond and half-delta plan form. Results regarding the effect of control area and plan form on control characteristics and on trim characteristics are provided.

"Curves and tabular data present the results of strength tests made during and after 2 1/2 years of aging on rivets and rivet wire of 3/16-inch nominal diameter. The specimens were of aluminum alloy: 24s, 17s, and a17s of the duralumin type and 53s of the magnesium-silicide type" (p. 353).

An experimental investigation to explore the practicability of a low-speed missile designed to fly with its longitudinal axis pointing along the flight path. The wing and tail surfaces were arranged in a cruciform pattern and the incidence was selected to trim the missile at the desired normal-force coefficient with the body at 0 degrees angle of attack. Results regarding the description of a self-balancing missile and experimental results are provided.

Report presenting an investigation of a model of the Chance Vought XF8U-1 airplane to determine the effect of spin-recovery rockets on the recovery characteristics of the model. The investigation also included tests to determine the effect of simulated engine thrust on the recovery characteristics of the model. Results regarding yaw rockets, thrust-simulation rocket, and roll rockets are provided.

Report discussing testing of a scale model of the Convair F-102B to determine its aerodynamic characteristics at several Mach numbers. Four basic body modifications and two afterbody configurations were evaluated.The body modifications were all found to slightly reduce values of minimum drag, but did not cause a change in the static stability and lift-curve-slope values compared to the F-102A.

Presentation at the National Western Mining Conference of the Colorado Mining Association, Denver, Colorado, February 7, 1959. Thank you for your invitation to discuss here today some of the aspects of nuclear explosions in mining and mineral industries. I should like this afternoon to dwell briefly upon: (1) The phenology of a nuclear explosion underground. What happens; with what energies are we concerned, and what may be the scientific and industrial results of such an explosion? (2) The safety or radiological hazards involved. If mining men hope someday to use this new and potentially useful source of packaged power, what are some of the problems we may face? First let me emphasize that the nine underground test explosions thus far have resulted in a wealth of data and interesting information which prove that radioactivity and radioactive fall-out can be completely controlled, that seismic effects are relatively minor, that appreciable amounts of heat and shock are generated, that this power might be utilized to serve a useful purpose and that the debris in an explosion area can be worked soon after the detonation.

The purpose of this report is to describe the tests performed on the D-12 waste evaporator, to present and evaluate the data obtained during the test, and to make recommendations for the implementation and operation of present and future installations of bayonet tube bundles.

It is the purpose of this report to: 1. Present the results of a study to estimate the range of attainable boiling conditions in the 1706 KER loop design on the bases given in reference (12). 2. Present an outline of the significant modifications and equipment changes necessary to obtain the process conditions desired.

Quarterly summary report of studies conducted through the Radiation Laboratory, University of California. Some results reported in the report may be of a preliminary or incomplete nature.

For an experiment to measure the magnetic moment of the Λ hyperon, it was necessary to extract the external beam of the Cosmotron with maximum efficiency and with minimum time duration. To accomplish this end, the standard external beam of the machine was supplemented with the Rapid Beam Ejector. It was found that, unfortunately, the ejection efficiency of the beam was less than normal when the RBE was used. Measurements of the ejection efficiency were made by irradiating polyethylene foils at the second focus of Beam 1 with 3 BeV protons. The external beam was tuned up and optimized in a standard manner. It was found that the ratio of the number of protons ejected with the RBE to the number ejected without the RBE was 0.3 in one run and 0.22 in another try. It was also observed that the RBE did not shift the position of the external proton beam focus to within ± 1/8 in.

Report presenting lift, drag, and pitching-moment coefficients, lift-drag ratios, and center-of-pressure positions for three highly swept three-wing tailless configurations determined from tests at a range of Mach numbers and angles of attack.

Memorandum presenting stability and control data from the X-4 airplane during the Northrop conducted acceptance tests. The data were obtained for a center-of-gravity position of about 22 percent of the mean aerodynamic chord. Results of the flight indicated that the airplane is slightly unstable, stick fixed, in gear-up, flaps-up configuration for a center-of-gravity position at 21.4 percent of the mean aerodynamic chord.

From Summary: "A preliminary investigation of the effects of changes in the elevator and rudder settings and of small changes in attitude upon the aerodynamic forces and moments exerted upon a spinning airplane was undertaken with the spinning balance in the 5-foot vertical tunnel of the National Advisory Committee for Aeronautics. The tests were made on a 1/12-scale model of the "NY-1" airplane. Data by which to fix the attitude, the radius of spin, and the rotational and air velocities were taken from recorded spins of the full-scale airplane."

"An investigation was conducted to correlate the engine service performance of cast Vitallium turbine buckets with standard laboratory metallurgical data. Data were obtained from four I-40 turbine wheels of Timken alloy with cast Vitallium buckets. In order to accelerate bucket deterioration, the turbine wheels were subjected to 20-minute cycles consisting of 5 minutes at idle and 15 minutes at rated speed" (p. 1).

A preliminary mathematical study is made of the maximum expected expansion of barium titanate ceramic. It is noted that there is insufficient physical evidence for a complete answer and some possible mathematical models are discussed and compared.

One of the considerations in designing a flat plate fuel element is the resistance of the fuel plates, especially the outer plates in the fuel plate array, to deflection and permanent deformation as a result of pressure differentials. An investigation was recently initiated wit the objective of obtaining preliminary information on the APPR-type fuel element to determine the effect of pressure differentials on the outer plates in the fuel assembly. The APPR-1 fuel element consists of 18 flat composite stainless steel fuel plates, joined to grooved 50 mil thick type 304L stainless steel side plates by brazing with Coast Metals N. P. alloy.

Small Heat Exchanger ORNL #1, type SHE #2, was removed form test stand B after 2071 hours of operation. Thirty-five samples were removed form the entire heat exchanger. The corrosion found on the outside of the tubes exposed to the fluoride mixture ranged to a maximum depth of .004 inches; however, the frequency of occurrence along the tube wall was heavier at the NaK outlet header, which was the hottest area in the heat exchanger. The depth of attack observed on the fluoride side of this heat exchanger was uniform from header to header and did not exceed .004 inches.