Commonwealth Edison Company for the purpose of supplementing the license application for the Dresden Nuclear Power Station submits herewith Amendment No.1 to the portion of the Final Hazards Summary Report entitled Preliminary Hazards Summary Report.

Somewhere in the future lies the possibility that the existing HAPO reactors will no longer be required for the production of weapons grade plutonium. This could come about either through advances in technology or through changes in the requirements for this particular fissionable isotope as a weapons material. In any event, should these reactors no longer be utilized for plutonium production, it would be appropriate to consider the possibility of their conversion to other uses, notably that of electrical power production. Accordingly, this study has been made with the objective of investigating the economic and technological feasibility of such conversion. However, it must be recognized that the results presented herein are based on present day technology and economic philosophy and that within the next five years we may experience considerable renovation of these criteria which could alter the conclusions of the study appreciably. The primary benefit to be gained from this preliminary study is to narrow the area of future and more detailed investigation as much as possible so that if and when such a conversion appears likely, a significant fraction of the almost infinite number of combinations of reactor and power plant parameters may be rejected at the outset.

A new method of introducing predetermined quantities of hydrogen into zirconium was developed and evaluated. The procedure is simple, effective, and inherently good in preverting oxygen and nitrogen contamination. Zirconium samples containing four levels of dissolved hydrogenated to 100, 300, 3500, and 7700 ppm hydrogen. Dissolved oxygen was found to decrease hydrogen absorption in both the alpha and beta modifications of zirconium. The effect of hydrogen on density, hardness, and microstructure was determined. X-ray-diffraction measurements were also obtained. (auth)

The study of interactions and decay of K mesons continued, using the 10- inch liquid hydrogen bubble chamber and emulsions. Four emulsion stacks were exposed for two internal groups and twenty-three stacks were exposed for seventeen groups from outside the Laboratory. Interactions of pi /sup -/ mesons were observed with a 30-inch propane bubble chamber and with emulsions. Ten emulsion stacks were exposed to neutral-particle beams and one stack to the internal 6.2-Bev proton beam. The 30-inch propane bubble chamber and emulsions were used to study the interactions of antiprotons. Eighteen target bombardments in the internal proton beam were made for the chemistry group. Successful tests were completed of two static-electromagnetic velocity spectrometers for the separation of highenergy particles. One was of coaxial construction, the other of parallel-plate construction. (For preceding period see UCRL-6114.) (auth)

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Will Wilson, regarding a legal question submitted for clarification: Proper method of taxing assets of a bank under submitted facts.

Report presenting an investigation to determine the longitudinal characteristics of an airplane model with a thin, highly swept and tapered wing of low aspect ratio equipped with plain leading-edge flaps in conjunction with blowing-type boundary-layer control applied to flap radius. Several leading-edge configurations and boundary-layer control system variables were also investigated.

Report presenting an investigation to measure and to compare the total-pressure recovery and distortion characteristics at the compressor face of two single-place fighter-type airplanes with similar two-spool turbo-jet engines, but with dissimilar inlets. Results regarding compressor-face total-pressure surveys and surges encountered are provided.

Report presenting an investigation to determine some effects of surface roughness on heat transfer at the stagnation point. Testing occurred in the ceramic-heated jet laboratory model at a Mach number of 2, a stagnation temperature of 3,530 degrees Fahrenheit, and a stream Reynolds number of 2.5 x 10(exp 6) per foot. Results regarding the variation of stagnation-point heat-transfer coefficient with surface roughness, heat transfer at the stagnation point of a hemisphere, and heat-transfer coefficient are provided.

Memorandum presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effects of forebody strakes on the aerodynamic characteristics in sideslip of a delta-wing airplane model at Mach number of 2.01. The presence of the strakes increased the directional-stability level for both vertical-tail arrangements. Results of pressure tunnels for a forebody show that the presence of the strakes provides a stabilizing influence on the forebody which is consistent with the results of force tests.

Report presenting a theoretical analysis of the supersonic flow about two-dimensional and three-dimensional axially symmetric models restricted by theoretical walls capable of removing the nose shock. Results regarding the supersonic-tunnel interference due to nonreflecting walls and supersonic-tunnel interference due to porous walls are provided.

Memorandum presenting a theoretical analysis of the supersonic flow about two-dimensional and three-dimensional axially symmetric models restricted by theoretical walls capable of removing the nose shock. Results regarding the supersonic-tunnel interference due to nonreflecting walls and supersonic-tunnel interference due to porous walls are provided.

Memorandum presenting an investigation conducted to measure and compare the total-pressure recovery and distortion characteristics at the compressor face of two single-place fighter-type airplanes with similar two-spool turbojet engines, but with dissimilar inlets. The total-pressure recovery was relatively independent of angle of attack and mass-flow ratio for both airplanes except for a significant decrease in pressure recovery with angle of attack for airplane B at the highest Mach numbers tested.