Memorandum presenting a pressure-distribution investigation of a wing of a complete supersonic aircraft configuration as conducted in the 4- by 4-foot supersonic tunnel at Mach number 1.59 based on the mean aerodynamic chord. The experimental life and drag coefficients were less than those predicted by linear theory. Results regarding section pressure characteristics, section characteristics, spanwise characteristics, and overall wing characteristics are provided.

"The rolling effectiveness of a thin, tapered, and essentially unswept wing having outboard partial-span plain ailerons has been determined by means of rocket-powered test vehicles. The rolling power decreased abruptly in the Mach number range from 0.85 to 0.95 and more gradually at higher speeds. At the maximum Mach number of the tests (1.95), the rolling effectiveness was only 20 percent of that at a Mach number of 0.85" (p. 1).

Report presenting testing of rocket-powered models flown at transonic speeds to determine the effect of nacelle location on zero-lift drag. Low drag was obtained between M = 0.80 and M = 0.91 for all the nacelle positions investigated. Nacelles located at the wing tips gave the lowest drag, which was less than the drag of the combination without the nacelles over most of the speed range.

The drag of a body alone, six triangular wings of various aspect ratios, and the combinations were measured at Mach numbers of 1.50 and 2.02 at a Reynolds number of 5.5 million (based on the body length). The experimental drag-interference results were in accordance with calculations based on NACA RM A9E19, 1949, with skin-friction effects taken into account, the interference effect being principally the result of fixing transition on the body by adding a wing.

Report presenting a study of a large amount of data pertaining to high-speed buffet boundaries of various airplane configurations. The data indicate a strong influence of wing configuration on buffet boundaries. Results regarding low-lift buffeting, high-lift buffeting, buffet boundaries, and buffet intensity are provided.

Report presenting a low-speed investigation in the stability tunnel to determine the effects of tail height, length, and aspect ratio on the static longitudinal stability and control characteristics of a 60 degree triangular-wing model with twin triangular all-movable tails located near the wing tips.

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"Preliminary results of one phase of a control-motion study program are presented in the form of plots of load factor.and angular acceleration against indicated airspeed and of time histories of several measured quantities. The results were obtained from 197 maneuvers performed by an F-86A jet-fighter airplane during normal squadron operational training. Most of the tactical maneuvers of which the F-86A is capable were performed at pressure altitudes ranging from 0 to 32,000 feet and at indicated airspeeds ranging from 95 to 650 miles per hour" (p. 1).

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Report presenting a compressor-rotor-blade vibration survey on a production turbojet engine incorporating a 13-stage axial-flow compressor with a pressure ratio of approximately 7 and an air flow of 120 pounds per second. The investigation was conducted due to the major problem that fatigue failures of compressor rotor blades have caused in the development of the axial-flow compressor. Results regarding rotating stall characteristics, rotor-blade vibration, and fourth-stage rotor-blade failure are provided.

A generalization of the Fermi-Thomas model for application of mixtures. This study attempts to determine the equation of state of water up to pressure of 10,000 megabars and temperatures of several thousand electron-volts.

This document presents a summary of work and progress at the Hanford Engineer Works for April 1955. The report is divided into sections by department. A plant wide general summary is included at the beginning of the report, after which the departmental summaries begin. The Manufacturing Department reports plant statistics, and summaries for the Metal Preparation, Reactor and Separation sections. The Engineering Department`s section summarizes work for the Technical, Design, and Project Sections. Costs for the various departments are presented in the Financial Department`s summary. The Medical, Radiological Sciences, Utilities and General Services, Employee and Public Relations, and Community Real Estate and Services departments have sections presenting their monthly statistics, work, progress, and summaries.

Report presenting an investigation of the overall performance of a modified eight-stage axial-flow compressor as part of the investigation of the problems encountered in a high-pressure-ratio axial-flow compressor with transonic inlet stages. The maximum total pressure ratio obtained at design speed was 11.0 at an equivalent weight flow of 70.9 pounds per second with an adiabatic efficiency of 0.81. Results regarding modified compressor performance and comparison with predicted performance are provided.

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"During an investigation of the J57-P-1 turbojet engine in the Lewis altitude wind tunnel, effects of inlet-flow distortion on engine stall characteristics and operating limits were determined. In addition to a uniform inlet-flow profile, the inlet-pressure distortions imposed included two radial, two circumferential, and one combined radial-circumferential profile. Data were obtained over a range of compressor speeds at an altitude of 50,000 and a flight Mach number of 0.8; in addition, the high- and low-speed engine operating limits were investigated up to the maximum operable altitude" (p. 1).

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Ultrasonic inspection for subsurface flaws is widely used in American industry. This report reviews the general principles and specific techniques of ultrasonic testing. The information is based on a review of the technical literature plus the experience of the Quality Assurance Department at Sandia Corporation in applying this nondestructive testing technique to quality evaluation programs.

The production of U/sup 232/ in the cost optimized TBR and oneregion thorlum oxide-uranium oxide slurry reactor has been estimated to be, respectively, 40 and 260 parts per million parts of U/sup 233/ produced. These production rates are compared with corresponding production rates in irradiated thorium rods and found to be comparable. Recommendations are made for increasing the purity of the U/sup 233/ product. (auth)

Letter opinion 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, John Ben Shepperd, regarding a legal question submitted for clarification; Constutionality of Senate Bill 161, 54th Legislature, amending Article 7065b-8, Vernon's Civil Statutes.

Report presenting a cycle analysis of a turboprop engine for various modes of operation over a range of flight conditions in order to determine whether one mode of operation has any marked advantages. The methods of operation explored included constant compressor equivalent design speed, constant design engine rotative speed, adjustable turbine stators, and variable exhaust-nozzle area.

Report of an investigation of the effect of mode of engine operation, engine configuration, and airplane flight condition on the performance and design requirements of a turboprop engine with a high-pressure-ratio single-spool compressor. Both single-spool engines and gas-generating engines are considered. The free-turbine engine was found to be less versatile than the single-spool engine because the range of turbine-inlet temperature over which it can operate is restricted.

"Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 to determine the static longitudinal stability and control characteristics of various arrangements of the Grumman F11F-1 airplane. Tests were made of the complete model and various combinations of its component parts and, in addition, the effects of various body modifications, a revised vertical tail, and wing fences on the longitudinal characteristics were determined" (p. 1).

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Report presenting the results of short-time creep-buckling and creep-bending tests of 2024-T4 aluminum-alloy columns of slenderness ratio 111 are presented. Tests were performed at 600 degrees Fahrenheit and strain measurements were taken with high-temperature electric-resistance strain gages.