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.

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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.

Report presenting testing using a 1 7/8-inch inside-diameter combustor that can measure and compare the blow-out velocities of single-component fuels, slurries, and fuel mixtures with a wide range of reactivity and physical properties. The blow-out velocities of isooctane, n-heptane, isopentane, allyl chloride, and propylene oxide varied int he same way as flame speeds of the fuels. Results regarding the effects of different additives are also 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.

Report presenting an investigation of two translating spike inlets with blunt- and sharp-lip cowls in the supersonic wind tunnel at a range of free-stream Mach numbers and angles of attack. Results regarding the inlet stability, critical inlet performance at zero angle of attack, and inlet-engine matching are provided.

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.

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.

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.

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.

The interaction of the flow from one convergent and two convergent-divergent nozzles on parabolic afterbodies was studied at free-stream Mach numbers of 2.0, 1.6, and 0.6 over a range of jet pressure ratio. The influence of the jet on boattail and base drag was very pronounced. Study of the total external afterbody drag values at supersonic speeds indicated that, over most of the high-pressure-ratio range, increasing the nozzle design expansion ratio increased the drag even though the boattail area was reduced. Increasing the pressure ratio tended to increase slightly the total-drag increment caused by angle-of-attack operation.

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 presenting an investigation to determine the effects of two spinner shapes on the pressure recovery in an NACA 1-series D-type cowl behind a three-blade propeller with fairly thick shanks. Data were obtained at a range of Mach numbers, inlet velocity ratios, blade angle ratios, and a specified Reynolds number.

Several failures have occurred in reduction bombs used in metal production operations. A test program is being initiated to evaluate new metals for the construction of the bomb. In the test program, a tensile specimen is cycled through temperatures simulating operating temperatures, and the time to rupture is recorded in order to estimate the life in operation of a reduction bomb made with the candidate metal. In order to find the worst stress condition, the compressive, hoop, and bending stresses must be considered.

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.

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.

This experiment was designed to furnish data on the quantitative relationship between exposure of enriched uranium metal to thermal neutron bombardment and the subsequent release of gaseous fission fragments from the metal. Studies of data obtained from the in-pile phase of the KAPL Fission Gas Experiment indicate, neglecting startup and shutdown transients, that gaseous fission fragments generated within a 6-mill foil of uranium metal maintained at an operating temperature of about 450 C are released from the foil nearly as fast as they are produced.

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.