From introduction: This report covers an investigation of solid-state bonding as a technique for aluminum cladding uranium plates of 3 by 0.180-in. cross section in lengths up to 14 ft.

Abstract: "A possible mechanism for the generation of magneto-hydrodynamic whirl rings near the center of the sun is described. The organic relation of the reflection of these whirl rings at the surface of the sun to the cooling of sunspots, orientation, and polarity sequence of sunspots, prominences, flares, and faculae is delineated."

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; Constitutionality of House Bill 211 of the 54th Legislature.

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; Constitutionality of House Bill 119, 54th Legislature authorizing creation of corporation courts in certain cities.

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; Effect of S.B. 34, 53rd Leg., upon transfer of compensation experience under provisions of Sec. 7(c)(7) of Texas Unemployment Compensation Act "subsection (c)(7), Art. 5221b-5, V.C.S.)

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, John Ben Shepperd, regarding a legal question submitted for clarification: Legality of obtaining Federal Old Age and Survivors Insurance coverage for county appointive officers and employees presently covered by a county retirement fund established pursuant to Article XVI, Section 62(b), Tex. Const.

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, John Ben Shepperd, regarding a legal question submitted for clarification: Effect of abolishment of an independent school district on existing teacher employment contracts.

This document comprises chapter four of nuclear metallurgy lectures. This chapter provides a discussion of pile components and related reactor kinetics.

Since the development of Dirac's theory of the electron and the brilliant confirmation of one of its most startling predictions by the discovery of the positron by Anderson, it has been assumed most likely that the proton would also have its charge conjugate, the antiproton. The properties that define the antiproton are: (a) charge equal to the electron charge (also in sign); (b) mass equal to the proton mass; (c) stability against spontaneous decay; (d) ability to annihilate by interaction with a proton or neutron, probably generating pions and releasing in some manner the energy 2 mc{sup 2}; (e) generation in pairs with ordinary nucleons; (f) magnetic moment equal but opposite to that of the proton; (g) fermion of spin 1/2. Not all these properties are independent, but all might ultimately be subjected to experiment.

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Report presenting the reverse-thrust performance of several tail-pipe-cascade-type model thrust reversers over a range of exhaust-nozzle pressure ratios from 1.2 to 2.4. Both symmetrical and asymmetrical cascade blade shapes were investigated. Results regarding the performance of tail-pipe-cascade-type model thrust reversers having symmetrically shaped cascade blades and the performance of tail-pipe-cascade-type model thrust reversers having asymmetrically shaped cascade blades are provided.

Report presenting an investigation of a wing swept back 35 degrees in combination with one basic body and three modified bodies at a range of Mach numbers from 0.60 to 1.20. Results regarding force studies and pressure studies are provided. The bodies modified according to the Kuchenmann ring-vortex method resulted in superior aerodynamic characteristics except with regard to zero-lift drag at high supersonic Mach numbers.

Report presenting an investigation of several methods of straightening diffuser-exit total-pressure profiles produced by a typical half-conical double-shock side inlet at a free stream Mach number of 3.05. The methods included the use of longer subsonic diffusers, constant-area mixing sections at the diffuser exit, internal screens, a rapid acceleration of the flow at the diffuser exit, internal bleed, and a change in internal-flow passage shape obtained by raising the internal centerbody fairing from the floor into the diffuser duct. Each of the methods was found to be effective in reducing distortion.

Report discussing testing on a model of the General Electric P-1 nuclear powerplant to determine its internal aerodynamic characteristics. The main purposes of testing were to measure the mass-flow distribution of air, to measure the total-pressure losses for the duct components and complete model, and to determine modifications necessary to attain the desired performance characteristics.

Report presenting an investigation of ram-jet-engine control by shock positioning on a 16-inch fixed-geometry ram jet at a range of free-stream Mach numbers. The control method appears to offer adequate control of ram-jet-engine operation. Results regarding the steady-state performance, effect of control settings on response and stability, effect of disturbance size and Mach number on response to fuel-flow disturbances, Mach number disturbances, angle-of-attack disturbances, exhaust-area disturbances, and recovery from subcritical engine operation are provided.

From Summary: "Experimental performance of a rocket engine using 15 percent fluorine-85 percent oxygen and JP-4 was compared with that obtained using oxygen and JP-4. The regeneratively cooled engine was operated at 5000 pounds thrust and a chamber pressure of 350 pounds per square inch absolute. The peak specific impulse from 15 percent fluorine was 251 pound-seconds per pound. This is an increase of 3.3 percent over the 243 pound-seconds per pound obtained with fluorine."

"A rapid design method based on stream-filament techniques was developed to obtain the boundaries of an annular combustor-inlet diffusr from a given stagnation streamline, given boundaries of the combustor liner, and given inlet and terminal velocities" (p. 1).

Report presenting an experimental investigation to determine the effect of rotor leading-edge sweepback on the aerodynamic performance of a transonic turbine. Using an unmodified stator with the modified rotor resulted in large incidence angles at the rotor mean and tip sections.

Report presenting an investigation of the performance of pentaborane fuel at relatively low equivalence ratios using a 9.75-inch-diameter ramjet engine using pentaborane at an average equivalence ratio of approximately 0.23. Time histories of the flight conditions and combustion chamber conditions, total-temperature ratio, fuel flow, pressure recovery, thrust, propulsive thrust, and drag coefficients, and comparison with hydrocarbon fuel are provided.

Report discussing an investigation of the supersonic area rule using rocket-propelled zero-lift models of straight wing-body configurations at a range of Mach and Reynolds numbers. The body was modified with symmetrical indentations according to area-rule considerations in order to reduce wave drag. The indentations were found to have an effect at Mach numbers 1.10 and 1.41 but did not have any benefit above Mach number 1.3.

Memorandum presenting an investigation to determine the static longitudinal and lateral stability and control characteristics of an airplane configuration with a trapezoidal wing with modified hexagonal airfoil section and tail surfaces with 5 degrees semiangle wedge sections carried out in the 11-inch hypersonic tunnel.

"A free-jet investigation of the performance of the XRJ43-MA-3 ram-jet engine has been conducted in an altitude test chamber at the NACA Lewis Laboratory. It is the purpose of this report to compare the performance and rich blow-out limits of the various engine configurations and diffuser orientations with the basic or standard engine configuration" (p. 1).