A report which intends to acquaint the reader with the planning of the radiochemical laboratory designed for the analytical control of the radiolanthanum process and to define the terminal status of the design of this laboratory and its equipment.

"The purpose of this present document is twofold: (1) To acquaint the reader with the planning of the radiochemical laboratory designed for the analytical control of the Radio-lanthanum Process. (2) To define the terminal status of the design of this laboratory and its equipment."

Abstract: "This is a detailed report on the circuitry, the electrical components, and the electrical engineering problems of Table Top I, the 140-kilojoule experimental model of a magnetic mirror machine being developed at the University of California Radiation Laboratory, Livermore."

Summary: "The quantity of water adsorbed by graphite at various relative pressures has been determined and the data are presented in graphical and tabular form."

Introduction: "The observations reported in this document were obtained by C.H. Pitt during his assignment to the Corrosion Group September through October 1951. The tubes examined were: 1.) 0893-F Discharged for corrosion examination after leaking; 2.) 1488-DR Discharged to determine caused of obstruction; 3.) 2276-D Discharged for corrosion examination; 4.) 2376-D Discharged for corrosion examination; 5.) 1185-H Discharged to evaluate the effect of magnesium front dummies."

Document 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, Will Wilson, regarding a legal question submitted for clarification: The authority of the Comptroller of Public Accounts to refund or give credit on future tax payments for overpayment of taxes on alcoholic beverages damaged or otherwise unfit for human consumption.

This document details activities of the irradiation processing department during the month of June 1958. A general summary is included at the start of the report, after which the report is divided into the following sections: research and engineering operations; production and reactor operations; facilities engineering operation; employee relations operation; and financial operation.

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The aqueous corrosion behavior of defected fuel elements having a U-2 wt. % Zr core with Zircaloy-2 cladding has been studied. A standard diffusion heat treatment for 7 hours at 880 C, followed by moderately rapid cooling, was established to overcome the effect of subtle defects in 15-mil Zircaloy cladding. The development of this heat treatment was carried out primarily with small rod specimens, which were also used to obtain data on aurxiliary effects of thw diffusion heat treatment. The heat treatment has been applied to full diameter tubes. One of these tubes was tested with subtle defects and various sections have been observed following the insertion of gross defects. These observations have shown a difference in the rate of hydrogen evolution as a result of heat treatment. In addition, the heat treatment changes the nature of failure in both full diameter tube sections and small rods. The presence of 2 wt. % Zr in the core reduces the corrosion rate considerably. Comparative quantitative data are presented for uranium alloys with various zirconium contents up to 15 wt. %. (auth)

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A flight investigation was made at altitudes of 40,000, 25,000 and 15,000 feet to determine the horizontal-tail loads of the Bell X-5 research airplane at a sweep angle of 58.7 deg over the lift range of the airplane for Mach numbers from 0.61 to 1.00. The horizontal-tail loads were found to be nonlinear with lift throughout the lift ranges tested at all Mach numbers except at a Mach number of 1.00. The balancing tail loads reflected the changes which occur in the wing characteristics with increasing angle of attack. The nonlinearities were, in general, more pronounced at the higher angles of attack near the pitch-up where the balancing tail loads indicate that the wing-fuselage combination becomes unstable.

Memorandum presenting a theoretical analysis of an airplane automatic control system incorporating a compensating network. The compensating network is a computing network that has characteristics that are the inverse of the airframe; consequently, airplane dynamics are eliminated from the system response. Results regarding the displacement control system, the velocity command system, and the acceleration control system are provided.

Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effect of changes in body cross-section shape on the aerodynamic characteristics of bodies and wing-body combinations. A series of 13 bodies of a given length and volume but various cross-section shapes were tested at a Mach number of 2.01. The results showed that changes in drag at zero lift due to changes in body cross-section shape from the basic circular shape are small and of the same order as the test accuracy.

Report presenting an investigation of aircraft which are required to maneuver rapidly at extreme altitudes, which involves reaching maximum loads at high angles of attack. Load information is necessary for that flight condition and for aircraft that reach their maximum loads at high speed and high dynamic pressures. Results regarding the wings and wing-body combinations are provided.

Memorandum presenting development tests on a 1/4-scale model of the Republic F-105 airplane in the 19-foot pressure tunnel. The tests in this particular report include longitudinal stability and control tests of the basic design provided by the contractor, tests of various modifications designed to improve the stability characteristics of the model with the trailing-edge flaps deflected, brief exploratory lateral-control and rudder-effectiveness tests, and stall studies and duct air-flow measurements.

Memorandum presenting the effects of deflected inboard ailerons on the wing loads of a 45 degree sweptback wing-body combination in the 16-foot transonic tunnel. The model had a wing with an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections. Results regarding the chordwise pressure distributions, effect of ailerons on wing section loadings, effect of aileron on wing loading, and effects of a deflected aileron on opposite-wing loading are provided.

Report presenting some experimental data and calculations for a variety of aerodynamic shapes considered for use as manned reentry vehicles. Three types of vehicles were tested: non-lifting bodies, lifting bodies, and airplane-like vehicles. All of the configuration types were found to be suitable for use as manned reentry vehicles with certain fin and flap modifications for certain shapes.

Report presenting a study of data from wind-tunnel investigations to determine the effects of thin chordwise fences on some of the aerodynamic characteristics of four moderately sweptback wings at a low-lift range. The fences caused no large detrimental effects on lift or pitching moment at transonic or supersonic speeds. Results regarding the increment of drag coefficient due to fences, effect of fences on the lift coefficient and longitudinal stability, and effects on aileron effectiveness are provided.

Experimental investigation of aerodynamic forces acting on body of revolution (NACA RM-10 missile) with and without stabilizing fins was conducted at Mach numbers from 1.49 to 1.98 at angles of attack from 0 to 9 degrees and at Reynolds number of approximately 30,000,000. Comparison of experimental lift, drag, and pitching-moment coefficients and center of pressure location for body alone is made with linearized potential theory and a semiempirical method. Results indicate that aerodynamic characteristics were predicted more accurately by semiempirical method than by potential theory. Breakdown of measured drag coefficients into components of friction, pressure, and base-pressure drag is presented for body alone at zero angle of attack.

"A brief study was made of the effects of slots in a test-section wall on the reflection from the wall of an incident oblique shock wave at a free-stream Mach number of 1.62. The reflection was observed with an interferometer for various combinations of slot width, spacing, and contour. The reflections from the open and the closed portions of the wall, being at different angles to the wall, were not superimposed and, therefore, did not cancel each other" (p. 1).

Report presenting pressure distributions measured along prolate spheroids of fineness ratios 3 to 20 and along a slender body of fineness ratio 12 are compared at subsonic and transonic speeds and several angles of attack. The experimental results, prediction of incompressible pressure distribution along the 0 degree and 180 degree meridians, prediction of subsonic pressure distribution along the meridians, prediction of subsonic pressure distributions around prolate spheroids, effect of fineness ratio and angle of attack on separation, and prediction of transonic pressure distribution.

Report presenting flight tests performed using the Douglas X-3 research airplane during the manufacturer's demonstration program and U.S. Air Force evaluation. Tests were performed over a range of Mach numbers and altitudes. Longitudinal, lateral, and directional stability and control data were obtained during steady and maneuvering flight and are compared with wind-tunnel and rocket-model data in this report.