Report presenting an investigation to determine the static lateral control characteristics of a supersonic aircraft configuration at Mach numbers of 1.40 and 1.59. The aileron effectiveness was about half of what was predicted by calculations, which was mainly due to flow separation in the region of the aileron. Information about other aileron characteristics and characteristics in sideslip is provided.

Report documenting the suitability of Florida for plant locations to produce synthetic liquid fuels, based on raw materials; however, it was concluded that there were no reserves of natural gas, and one producing oil field.

Report documenting the suitability of New York for plant locations to produce synthetic liquid fuels, based on raw materials, water sources, and local interest.

Report discussing testing to determine the supersonic aerodynamic characteristics of four sweptback wings and wing-body configurations at several angles. Information about basic wing data, modifications to the 60 degree wing, the effects of sweep, and effects of fuselage are included.

Objective: The objective of this study is to develop a simple method of either removing the C1- ion from the RAW or converting the ion into a less corrosive valence state.

Memorandum presenting a procedure for obtaining qualitative information on the effectiveness of different slot configurations to make the flow of the cooling air visible. Two methods are utilized: one utilizes the traces caused by a reaction between paint spread over the blade surface and a gas mixed with the cooling air, while the other utilized smoke mixed with the cooling air to make it visible. From the visual observations, the use of a continuous slot as a means of creating the cooling film over the blade surface appeared to be superior to the use of holes or grooves.

Memorandum presenting an investigation of a series of wing-fuselage configurations to determine the effects of wing geometry on aerodynamic characteristics. This paper presents the force, moment, wake, and downwash measurements made on a fuselage and wing-fuselage combination of specified measurements. The current phase of the investigation is focused on varying the sweepback of the 0.25-chord line of the wing.

Memorandum presenting an investigation of the interference at the root of a sweptback wing at high subsonic Mach numbers by means of wind-tunnel measurements of a wing-body combination with the 50-percent-chord line of the wing either unswept or swept back 35 degrees. Results regarding body characteristics, pressure studies, tuft studies, and force studies are provided.

Report presenting testing of a rocket-powered model of a fin-stabilized parabolic body of revolution with fineness ratio 8.91 and maximum diameter at 80 percent of body station at a range of Mach numbers to determine the static pressures at two orifices on the rearward side of the stabilizing fins. Results regarding measured pressures, comparison of theory and experiment, and drag are provided.

An altitude-chamber investigation of British Rolls-Royce Nene II turbojet engine was conducted over range of altitudes from sea level to 65,000 feet and ram pressure ratios from 1.10 to 3.50, using an 18.00-inch-diameter jet nozzle. The 18.00-inch-diameter jet nozzle gave slightly lower values of net-thrust specific fuel consumption than either the 18.41- or the standard 18.75-inch-diameter jet nozzles at high flight speeds. At low flight speeds, the 18.41-inch-diameter jet nozzle gave the lowest value of net-thrust specific fuel consumption.

"A complete stage of an axial-flow compressor designed to produce a high pressure ratio was investigated at speeds from 110 to 130 percent of design speed (836 ft/sec). The data obtained and the results of a previous investigation of the same compressor at speeds from 50 to 100 percent of design speed were used to determine the effect of Mach number on over-all performance. The peak total-pressure ratio increased from 1.095 to 1.515 and the peak adiabatic efficiency decreased from 0.93 to 0.89 as the relative inlet Mach number increased from 0.34 to 0.77. At a relative inlet Mach number of 0.91, a total-pressure ratio of 1.635 was obtained at an adiabatic efficiency of 0.74" (p. 1).

The use of inlet guide vanes with the 24-inch supersonic compressor resulted in a decrease in maximum pressure ratio and adiabatic efficiency, and a slight increase in equivalent mass flow. The loss in total pressure and efficiency resulted from reduced diffusion in the rotor-blade passages, increased shock losses at the higher entrance Mach number, and increased mixing separation, and transfer of mass flow toward the rotor hub. The unsteady flow field created at the compressor entrance by the guide-vane wakes is also responsible for some of the losses. This inherent loss will be encountered whenever inlet guide vanes are used with the shock-in-rotor type of supersonic compressor.

"An investigation is made of the buckling of the compression cover of post-stiffened box beams subjected to end moments. Charts are presented for the determination of the minimum post axial stiffnesses and the corresponding compressive buckling loads required for the compression cover to buckle with nodes through the posts. Application of the charts to design and analysis and the limitations of their use are discussed" (p. 1087).

From Summary: "Procedures for applying these analytical methods to experimentally measured blade-metal temperatures are presented. Data are presented for the leading and trailing edge of a symmetrical water-cooled blade to illustrate the validity of the methods for those portions of the blade. In addition to the application to turbine blades, the methods can be applied to any heat-transfer apparatus having a profile that can be approximated by the shape discussed."

The purpose of this report is to summarize the work done at KAPL on physical properties of high density concretes.

The following report discusses the results of a survey that was initiated to ascertain the availability of uranium hydride in tonnage quantities.

The following report describes methods used to determine tributylphosphate in a deodorized shell base. An infrared absorption method is developed to emphasize toward determination of TBP in RCW streams, the organic waste streams.

Report presenting exploratory testing obtained with leading-edge wing chord-extensions on two 52 degree sweptback wings. The wings had the same aspect ratio but different airfoil sections. Results regarding force characteristics and flow characteristics are provided.

Report presenting an investigation using the transonic-bump method through a range of Mach numbers in the high speed 7- by 10-foot tunnel to determine the lateral-control characteristics of 30-percent-chord flap-type controls with various spans and spanwise locations. Rolling moments, pitching moments, and lift were obtained through a small range of control deflections.

Abstract: A tungsten tipped electrode has been used in the continuous casting arc furnace for a 25 minute period during which a 12 inch length of ingot was made. Thermocouple junctions within the mold wall have been improved to give mold zone temperature. A total of 10 iodide dissociation runs have been conducted using feed rates of .62-22.7 lbs ZrI₄ per hour with attendant conversion efficiencies of 97.7-16.4% and zirconium yields of 255-41.2 grams per hour. A curve expressing these data for an arbitrarily selected set of conditions is presented.

Report presenting an investigation of a rectangular wing with a subsonic-type round-leading-edge airfoil section (NACA 65-009) at various Mach numbers. The results generally agreed with calculated values with the exception of the laminar-separated region on the low-pressure surface of the model. Results regarding the calculation of pressure distribution, experimental pressure distributions, aerodynamic characteristics, and shadowgraph studies are provided.

Report presenting an analysis of the flow conditions downstream of a cascade of turbine rotor blades at critical and supercritical pressure ratios. Five theoretical methods are compared with an experimental method using the conservation-of-momentum principle and static-pressure surveys as well as schileren photographs of the flow downstream of the blades. Results regarding static-pressure surveys and schileren photographs are provided.

An investigation of turbojet-engine thrust augmentation by means of tail-pipe burning has been conducted in the NACA Lewis altitude wind tunnel.

Introduction: "The adoption of aluminum nitrate as salting agent in the Redox process made it imperative that a method be available for determining plutonium in the presence of aluminum. However, large amounts of aluminum have been found to interfere with the determination of plutonium by the lanthanum fluoride procedure. Previous attempts to increase the accuracy of the lanthanum fluoride method, by precipitating LaF3 from 4 M HF (rather than 2 M), have been successful only when the initial plutonium level was high."