Abstract: "A method has been devised and successfully used for marking a leaking pile process tube prior to its removal from the pile, such that subsequent location of the leak is more easily accomplished. An acetone solution of Testor's Dark Red Airplane Dope is poured into the suspect tube. The solution leaks from the hole and stains the surrounding area a light pink. To date the method has been used on tubes 3573F, 0486F, 0867F, and 3670F."

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, Price Daniel, regarding a legal question submitted for clarification: "Period of litigation" of Sun Oil Company, et al v. Humble Oil & Refining Co., et al, under Article 5421i, V.C.S.

This report endeavors to point out the radiation hazards involved with respect to the patient undergoing oral roentgenography. The dose rate can be as high as 280 r/min. Very definite hematological changes have been observed and are being thoroughly investigated. Recommendations have been suggested to eliminate overexposures.

Introduction: This is the third of a series of memoranda concerning the statics of the teapot, a small-scale boiling reactor experiment, and covers power coefficients of reactivity, energy coefficients of fluid density, the poisoning effects of fission products, and production of gases. The numbering of the equations, figures, and tables thus follows that of CF 52-6-118.

This report presents information pertaining to the life of the reduction bombs in both the RG and RMM Lines of the Plutonium Purification and Fabrication operations in the 234-5 Building. The expected average life to rupture of the RG Line Bomb of carbon steel subjected to an internal pressure of 450 psig is ten hours at 750 C. The expected average life of the RM Line bomb of V-36 alloy is more than 100,000 hours at 750 C under the same operating conditions. These expected average life values do not include any calculated factor of safety. Since they are average figures, some bombs could be expected to have shorter life to rupture. The BG Line bomb of carbon steel is definitely hazardous under the extreme service conditions of 450 psig and 750 C. If the use of carbon steel is to be continued it is recommended that the bombs be redesigned to reduce unit stresses.

A slug of air-saturated distilled water was circulated for 317 hours at a velocity of 15 feet per second in an AISI 347 stainless-steel toroid with a wall temperature of 500 F and a 30 F difference in temperature between the hot and cold sections. The depth of corrosion layer was 0.001 inch (0.028 in./yr) in the hot sector and 0.0007 inch (0.019 in./yr) in the cold sector; no mass transfer was observed. The results of gas,water,and X-ray diffraction analyses are given together with photomicrographs of sections taken from the hot and cold sections of the specimen.

Report presenting an experimental investigation of the flow field downstream of a canard-type control surface and in the vicinity of a symmetrical body in the 8- by 6-foot supersonic tunnel at Mach numbers of 1.8 and 2.0. The results indicated severe total pressure losses and large flow deflections in the control surface wake.

"An investigation of the use of solid fences installed on the side walls of a supersonic wind tunnel to retard the development of transverse flow and thus to increase the uniformity of the side-wall boundary layer is reported. Beneficial results were obtained with fences which had depths of the order of the boundary-layer displacement thickness and which followed potential-flow streamlines through the nozzle. Reduction of the number of fences on each side wall from four to two eliminated their effectiveness" (p. 1).

Memorandum presenting a small-scale investigation of the effects of full-span and partial-span leading-edge flaps on the aerodynamic characteristics of a sweptback wing in the 7- by 10-foot tunnel over a Mach number range of 0.70 to 1.10. Lift, drag, pitching moment, and bending moment were obtained for the basic wing and for the wing with full-span and partial-span leading-edge-flap deflections of approximately 3, 6, and 9 degrees.

Report presenting an experimental investigation to determine the performance of twin-scoop side inlets located on the fuselage of a proposed aircraft in a region of large boundary-layer thickness. Inlet configurations with subsonic and supersonic cowlings which utilized two-dimensional compression ramps and ram-type scoops for boundary-layer-removal systems were investigated at several Mach number ranges. Results regarding supersonic Mach number range, angle of attack, subsonic Mach number, and static conditions are provided.