Report presenting an investigation to determine the temperature and pressure distributions in the jets issuing from two parallel nozzles of a turbojet engine located close together and impinging on the ground at an angle of 20 degrees. Results regarding the jet-nozzle pressure ratio, constant-temperature parameters, and temperature contours are provided.

From introduction: The present report describes further refinements of the apparatus and the method to meet a need for a sensitive determination of carbon in plutonium.

Memorandum presenting an investigation of a 2:1 area-ratio diffuser of length equal to the inlet diameter with several arrangements of simple rectangular vortex generators over a speed range up to an inlet Mach number of 0.5. The investigation was for an inlet boundary layer of 5 percent of the inlet diameter, a condition for which this diffuser had substantial separated areas with no vortex generators. Results regarding the diffuser with no vortex generators, counterrotating vortex generators, other arrangements investigated, and a comparison with results from previous diffuser research are provided.

Report summarizing data from Purex tests for pulse column specifications. These test results were used to estimate pilot plant specifications.

"The frequency of blade temperature to exhaust gas temperature is presented for two locations in the blade and at several operating conditions. The frequency response was determined by Fourier analysis of transient data. Two analytical methods are presented, and results are compared with experimental data. Dynamic response of turbine-blade temperature to exhaust-gas temperature exhibited the form of an approximate first-order lag" (p. 1).

Friction and surface damage of several materials that are resistant to corrosion due to liquid metals was studied in air. The values of kinetic friction coefficient at low sliding velocities and photomicrographs of surface damage were obtained. Appreciable surface damage was evident for all materials tested. The friction coefficients for the combinations of steel, stainless steel, and monel sliding against steel, stainless steel, nickel, Iconel, and Nichrome ranged from 0.55 for the monel-Inconel combination to 0.97 for the stainless-steel-nickel combination; for steel, stainless steel, monel, and tungsten carbide against zirconium, the friction coefficient was approximately 0.47.

Report presenting an investigation of some of the factors that affect autopilot systems in airplanes.

Theoretical performance for mixture of 36.3 percent liquid ammonia and 63.7 percent hydrazine with liquid oxygen bifluoride as rocket propellant was calculated on assumption of equilibrium composition during expansion for a wide range of fuel-oxidant and expansios ratios. Parameters included were specific impulse, combustion-chamber temperature, nozzle exit temperature, composition mean molecular weight, characteristic velocity, coefficient of thrust and ratio of nozzle-exit area to throat area. For chamber pressure of 300 pounds per square inch absolute and expansion to 1 atmosphere, maximum specific impulse was 295.8 pound-seconds per pound. Five percent by weight of water in the hydrazine lowered specific impulse from about one to three units over a wide range of weight-percent fuel.

Summary: A method was found for determining calcium concentrations in TBP process streams in spite of serious interferences bysodium, ferrous, uranyl, sulfate, phosphate, and sulfamate ions as well as by TBP. The precision attainable varied from sample to sample, depending upon its composition. In general, errors of 20% or greater occurred. The smallest determinable amount of calcium was about 10 mg/1.

Report presenting an investigation of the influence of high-altitude supersonic flight on the operation and effectiveness of turbine-blade liquid-cooling systems for application in turbojet engines in guided missiles and in supersonic aircraft. The problems encountered in liquid-cooling systems were investigated with reference to several specific designs for alternate heat-rejection mediums.

"During the flight program on the Bell X-5 airplane with 59 degrees sweepback to determine the practical Mach number and normal-force coefficient limits of this configuration, a reduction in static longitudinal stability was encountered in maneuvering flight. A determination of the boundary for reduction of longitudinal stability extending to a Mach number of 0.98 is presented in this paper. A reduction of static longitudinal stability existed for all elevator and all stabilizer-executed maneuvers" (p. 1).

This report presents the final results from the investigation of the ratio of Pu-239 fission cross section to U-235 fission cross section. Three sets of plutonium and uranium foils were prepared at KAPL and were investigated to acquire the final results.

This report describes the progress on the experimental breeder reactor. It focuses on the approach to critical experiments, calibration of controls and flues and flux distributions.

Memorandum presenting tests of a triangular-wing-airplane model equipped with high-lift devices and lateral and directional controls. The model consisted of an aspect ratio 4 triangular wing in combination with a fuselage of fineness ratio 12.5, a thin, triangular, vertical tail with a constant-chord rudder, and a thin, unswept, all-movable horizontal tail. Results regarding the effects of flap deflection and tail incidence on the pitching moment characteristics, lift and drag characteristics, and rudder effects are provided.

Abstract: "UO2 and ThO2 form a continuous series of solid solutions with the solidus-liquidus from 2875 C for UO2 to above 3200 C for ThO2."

From Introduction: "The purpose of this paper is to discuss and evaluate some of the input signals or control parameters which have been experimentally employed to operate turbojet inlet-control systems. These include the normal-shock position, the oblique-shock position, and the diffuser-exit Mach number. The discussion is based on results obtained at the NACA Lewis laboratory during control investigations of ram-jet engines (ref. 1 to 5) and during a study on the control of a supersonic inlet for the J34 turbojet engine (refs 6 and 7)."

Report presenting an investigation of the effects of rocket-armament-exhaust-gas ingestion on the performance of a supersonic-inlet J34-turbojet-engine installation at Mach 2. Rockets were fired from two different spike positions and with the engine at high or low speed. Results regarding engine air flow, temperature, and flame-out are provided.

Report presenting an investigation of three pairs of 1/10-scale Republic F-105 airplane wings at subsonic to low supersonic speeds in free flight by utilizing rocket-propelled models to investigate the possibility of flutter. The wing plan form was swept back 45 degrees at the quarter-chord line and had an aspect ratio and taper ratio based on the exposed panels of 2.92 and 0.5, respectively. Testing did not show the existence of flutter for the full-scale wings in clean condition up to Mach number 1.47.

Memorandum presenting a correlation of analyses of the effect of distributed surface injection on the heat transfer and skin friction associated with the turbulent boundary layer at high speeds to eliminate the effects of Mach and Reynolds number. Data for heat transfer and skin friction at three Mach numbers are compared with the analyses and the agreement is good.

Report presenting an experimental investigation in the transonic blowdown tunnel to determine effects of center-of-gravity location on the transonic flutter characteristics of a 45 degree sweptback-wing plan form of aspect ratio 4.0 and taper ratio 0.6. Solid-construction models with streamwise NACA 65A004 airfoil sections and center-of-gravity locations at three different chords were fluttered at a range of Mach numbers.

The HRT leak detector system consists of four headers each of which are connected on one side to a common supply of pressurized water and on the other side by individual tubing to the ring grooves of approximately twenty flanges. There are two methods of detecting the loss of water that are particularly applicable to the HRT: (1) By the loss of pressure in a constant volume system; (2) By the measurement of flow from a constant pressure system. It was determined to investigate the second method which requires a flowmeter capable of measuring flows of .5 cc or less of water per hour. The experiment flowmeter constructed performed almost exactly as the design calculations predicted.

Report issued by the APDA regarting studies conducted on the state of uranium at different temperature and pressure. Calculations are presented for the differing pressures of uranium; it includes tables.

Purpose: A reconnaissance was conducted during parts of August and September, 1956, of an area about two miles square in the southern Carrizo Mountains where the Permian Cutler formation, including its DeChelly member, and the Triassic Shinarump member of the Chinle formation, are exposed. The purpose was to appraise the uranium potential of the area and to determine the cause of bleaching in the DeChelly. Extensive uranium mineralization in the Salt Wash member of the Morrison formation around the Carrizo Mountaind suggested that the Shinarump, a good producer in other areas on the Colorado Plateau, might be mineralized here as well. Bleaching, as shown in the DeChelly; has proven such a useful guide to uranium at other localities as to merit investigation here.

Report discussing the aerodynamic loading characteristics of a 45 degree sweptback wing with leading-edge chord extensions, including the effects of a spoiler-slot-deflector aileron. The wing section loading, wing-panel loading, and chord-extension loading are described.