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This is the second of a series of documents issued quarterly. The documents present, for critical examination by management and for the information of related groups, that portion of the future 100 Area technical program which relates directly and more or less immediately to the Technical-Manufacturing efforts to increase both power levels and production. An attempt is made to describe and justify the key production tests planned for the following six month period. Only those tests necessary for the relief of technical and process limitations and vital to the slug improvement program are included. Best estimates of changes in current Process Specifications during the ensuing six months are also given. To further longer range planning, power level forecasts based on foreseeable changes of technical limits and scheduled physical changes of the water plants and reactors are extended several years into the future.

Report presenting normal-force and pressure distributions for a body of revolution consisting of a fineness-ratio-3, circular-arc, ogival nose tangent to a cylindrical afterbody 7 diameters long. Comparisons of theoretical and experimental distributions indicate that available theoretical methods are only accurate for angles of attack up to about 5 degrees.

Memorandum presenting a comparison made between the incremental aerodynamic root bending moments on the horizontal tail of a jet-powered bomber airplane measured during a flight investigation over a range of Mach numbers and the bending moments calculated by using available theoretical models in conjunction with measured loads, elevator positions, and elevator and stabilizer twists. Results regarding abrupt maneuvers, gradual turn maneuvers, and effects of downwash are provided.

Report presenting an investigation in the high-speed 7- by 10-foot tunnel to determine the effects of a wing leading-edge modification on the effectiveness of a spoiler-slot-deflector control. The modification consisted of a chord extension over the outboard 35 percent of the semispan in combination with a full-span leading-edge flap deflected 6 degrees.

Every type of thermal insulating material tested showed attack in varying degeces. Many specimens which had been cured at 1000 deg F, with no color change, did show drastic changes at 950 deg F due to the action of sodium. The materials showing the least disintegration and greatest preservation of mechanical properties were Superex paste and Eagle-Picher mineral wool. The uncured Superex Block did not hold up as well as Superax paste, presumably due to the presence of water of crystallization; after curing, the results were similar to that of the paste. The refractory clays showed the greatest degree of destruction. The time element is of vital importance, since a long perfod of contact with liquid sodium would presumably result in complete destruction of every specimen tested. (auth)

Report discussing an investigation to determine the aileron effectiveness and damping in roll of the Hughes Falcon missile, D configuration at several Mach numbers. Information about the rolling-moment coefficient, damping-in-roll derivative, and drag coefficient is provided.

Report presenting a free-flight investigation over a range of Mach numbers near zero lift to determine the aileron effectiveness and damping in roll of the full-scale Hughes Falcon missile, D configuration.

To determine, by test, the feasibility of decreasing the time requirements to prepare the aluminum clad uranium slugs into uranyl nitrate solution suitable for the separation of plutonium from uranium in the extraction step.

Report presenting an investigation to obtain forced-convection heat-transfer and pressure-drop data for flow of air between electrically heated parallel flat plates stacked to form passages of short length-to-effective-diameter ratio. The primary purpose of the investigation is to determine the interference effects of the upstream stack of plates on the heat-transfer and friction characteristics of the downstream stack. Results regarding the plate temperature gradients, heat-transfer data, and friction data are provided.

Tube 1794-C was removed from the pile as a leaker on July 15, 1954. The tube had been in-pile since startup and had contained a charge of 32 ``C`` metal slugs just prior to discharge. The tube was slit and examined at the 105-DR underwater viewing facility by Pile Coolant Studies tube examination personnel. A report is made of the examination of tube 1794-C which revealed areas of severe pitting damage. This damage was apparently caused by cocked slugs abrading the tube. The attack was great enough to cause perforation of the tube at about 27 feet from the rear Van Stone flange. Examination of the slugs showed that a considerable number had been cocked. Evidence of severe tube scarring and rib grooves was found on the slugs. Strikingly similar examples of pitting and grooving were observed on flow laboratory minitubes and slugs exposed in high velocity water. It is concluded that the damage observed both in- and ex- pile was caused by the chattering of misaligned low density slugs in a high velocity stream. If the number of in-pile occurrences of this attack becomes excessive it is recommended that the water flow rate in tubes containing ``C`` metal slugs …

Report presenting an experimental study of the compression fields around axially symmetric isentropic spikes with varying degrees of compressive flow turning made at a Mach number of 3.85 to analyze the basic shock structures and thereby establish further design criteria for supersonic-inlet applications. Results regarding the original isentropic spike and cowl, isentropic survey-spike configurations, and external-compression limitations are provided.

Portions of the Hanford Reservation in 1954 had significant particulate contamination from the Redox process. This paper is about the methods used to decontaminate the Reservation. The two methods are decontamination and access control. A general description of the ideas and benefits of each method is given. (MB)

Memorandum presenting cooling data for a transpiration-cooled afterburner with a porous combustion-chamber wall of brazed and rolled wire cloth for a range of exhaust-gas temperatures, total flow ratio of cooling air to combustion gas, and pressure altitudes. Maximum wall temperatures based on the cooling correlation were determined for a porous wall of uniform permeability at sea-level takeoff and for several flight Mach numbers. Results regarding typical data, cooling correlation, transpiration-cooling performance, comparison of transpiration and forced-convection cooling, and pressure environment of wire cloth are provided.

Report presenting cooling data for a transpiration-cooled afterburner with a porous combustion-chamber wall of brazed and and rolled wire cloth for a range of exhaust-gas temperatures, total flow ratios of cooling air to combustion gas, and pressure altitudes. Results regarding typical data, cooling correlation, transpiration-cooling performance, comparison of transpiration and forced-convection cooling, and pressure environment of the wire cloth are provided.

This report describes the direct essential material requirements for processing a standard run through the precipitation separations process in effect on August 1, 1954. Flow sheet conditions are based on a starting maximum batch size of 300 grams of product at a uranium irradiation level of 215 MWD/ton. The essential material requirements are those used to process with 2.5 grams of Bismuth per liter in Extraction, First Decontamination Cycle volumes at 56% of the September 1, 1946 standard, and Second Decontamination Cycle through the Lanthanum Fluoride Product Precipitation volumes at 49% of this standard.

Report presenting the performance of a twin-duct air-intake system utilizing a double-oblique-shock inlet with a variable second ramp at several Mach numbers. Testing was conducted over a range of angles of attack and yaw, mass-flow ratio, and variable-ramp angle.

From Summary: "Lateral and longitudinal combustion-pressure oscillations that occurred in screaming combustion of a 1000-pound-thrust rocket engine using white fuming nitric acid and JP-4 fuel as propellants were successfully prevented by means of longitudinal fins in the combustion chamber. Fin position was critical, and complete attenuation was achieved only when the fins were located in a zone approximately 8 to 16 inches from the injector. Fins located in other zones, that is, near the injector or far downstream from the injector, did not stop the oscillations."

Report presenting an experimental investigation on eight double-shroud ejector configurations with a current production-type turbojet engine and an afterburner as the primary gas generator. Air-flow and thrust characteristics of each ejector configuration are presented for a range of operating pressure ratios and weight-flow ratios at representative nonafterburning or afterburning primary gas temperatures.

Data were obtained in an altitude test chamber for a range of altitudes from 20,000 to 58,000 feet at a flight Mach number of 0.9, and for several flight Mach numbers at an altitude of 45,000 feet. Data approximating sea-level operation are also included. Engine component performance data are presented in addition to windmilling, exhaust-nozzle, and ejector performance.

The objective of this test is to establish that scavenging of first-cycle wastes in the Bismuth Phosphate Plant will give a supernatant liquor, after the precipitate settles, that may be routinely cribbed. This test will also perform the functions: establish an effective scavenging procedure, shakedown the pH monitor, and train operational personnel. This document discusses test procedures and results.

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This report lists pertinent NACA papers presenting research results which have a direct bearing on control system design and performance for both piloted and automatically controlled aircraft. Limited reference is also made to NACA reports on aircraft engine controls and to research techniques and instrumentation pertinent to the study of control systems and aircraft dynamics in flight. Reports published between January 1949 and April 1954 are listed in chronological order and cross referenced.

Memorandum presenting the compatibility of pentaborane with aluminum foil, 24S-T and 17S-T aluminum, and 50-50 tin-lead solder in the range of -30 to -50 degrees F for 7 hours, at 90 degrees F for 6.5 hours, and at 70 degrees F for 28 days. Results were evaluated by determination of the loss in weight after the test period, metallographic inspection, and comparison with blanks carried through test conditions without exposure to the liquid. The evaluation of results was made by visual inspection and physical tests of dimensional stability, tensile strength, elasticity, and gain or loss of weight.