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: Provisions of the Supplement to House Journal, Page 163, Sec. 3, and Article 634a, Sec. 3 V.C.S., as it relates to collection of monies and the re-appropriation for use for specific purposes as such collection of funds and appropriation for use relates to activities of the Board of Control.

Studies are under ray in Chemical Research and Development to-provide the technical ``know-how`` necessary to calcine Purex 1WW and safely store the solid product. The solid product can be stored as the particulate solid from the calciner or, after further treatment, as a solid matrix or melt. In this regard, Chemical Research is studying a PO{sub 4}BO{sub 2} melt. This document presents expected fission product heat generation rates in the solid product, shows the effect of various variables on heat transfer in the stored solid, and emphasizes certain items for further study. Also a vault cooling method is suggested for further study.

The elastic differential scattering cross section of 190 MeV deuterons by protons has been measured from 15 degrees to 170 degrees in the center of mass system. The cross sections were obtained by subtracting the carbon counts from those received with a polyethylene target. Part I presents a description of the experiments. Results are shown in Table IV and Fig. 3. Part II compares these results with those expected from theory by making use of a method developed by Chew. A summary of this comparison is given in Table VII.

Report discussing tests on a helicopter rotor powered by ram-jet engines located at the rotor blade tips. Information about the basic hovering characteristics of the rotor and the propulsive characteristics of the ram-jet engine were obtained over a range of speeds and fuel rates. Results were also obtained in the power-off condition and with the engines removed.

Memorandum presenting an investigation of a can-type flame holder employing a fuel-air-mixture control sleeve in a 20-inch-diameter ramjet combustor conducted by free-jet and direct-connect techniques at a simulated flight Mach number of 3.0 and altitudes from about 70,000 to 80,000 feet. Results regarding the effect of shortening combustion chamber and effect of pilot-burner variables are provided.

Memorandum presenting an investigation of the effect of the number and width of annular flame-holder gutters on afterburner performance in a 26-inch-diameter afterburner test rig. The burner inlet temperature was held at 1250 degrees Fahrenheit. Results regarding the effect of gutter width on stability limits and effect of flame-holder blockage on pressure drop are provided.

Report presenting an investigation of the effects of afterburner-inlet total temperature, total pressure, velocity, fuel-air ratio, and afterburner combustion-chamber length on afterburner performance and stability limits using a cylindrical afterburner installed in a duct test rig. The afterburner was investigated over a range of total temperature, total pressure, velocity, and afterburner fuel-air ratios.

The performances of Navy Jet Mix and MIL-F-5624A (JP-3) fuels were compared in J33, J47, and NACA experimental annular combustion chambers. Combustion efficiencies, altitude operational limits, and carbon-forming tendencies wer determined and discussed. The results indicate that Jet Mix fuel can be utilized satisfactorily in a number of current turbojet engines over the normal operating range. Small differences in combustion efficiences and altitude operational limits existed between the two fuels but these differences depended on the particular combustor and simulated altitude and rotor speed condition. Excessive carbon deposition is not predicted for Jet Mix fuel, although this property may be marginal.

Report presenting an investigation of the effect of the number and width of annular flame-holder gutters on afterburner performance in a 26-inch-diameter afterburner test rig. A 1-ring, 2-ring, and two 3-ring flame holders were investigated over a range of fuel-air ratios. Results regarding the effect of number of annular v-gutters on combustion efficiency, effect of gutter width on stability limits, and effect of flame-holder blockage on pressure drop are provided.

"Flat 2024-T3 aluminum panels measuring 11 inches by 13 inches were tested in the near noise fields of a 4-inch air jet and turbojet engine. The stresses which were developed in the panels are compared with those calculated by generalized harmonic analysis. The calculated and measured stresses were found to be in good agreement. In order to make the stress calculations, supplementary data relating to the transfer characteristics, damping, and static response of flat and curved panels under periodic loading are necessary and were determined experimentally. In addition, an appendix containing detailed data on the near pressure field of the turbojet engine is included" (p. 703).

Report presenting an investigation of the effectiveness of transpiration cooling on an 8 degree total-angle conical body with a porous skin for various coolant mass flow rates of nitrogen gas, helium gas, and distilled water.

Report presenting seven pairs of wings tested at Mach numbers of 1.63, 1.93, and 2.41 to determine the validity of NACA TN 2858, which predicts that delta wings with linearly varying thickness ratio have less wave drag than a constant-thickness-ratio delta wing. Results regarding the zero-lift wave drag, values of lift, total drag, pitching moment, and lift-drag ratios for an angle of attack range are provided.

Abstract: "The results of this investigation that it is necessary to remove fluoride prior to precipitation zirconium with mandelic acid or phenyl arsonic acid. Fluoride, however, has little effect on the cupferron method of precipitation. The discovery that zirconium fluoride is soluble in a mixture of aqua regia and sulfuric acid made it possible to dissolve the material without the addition of fluoride from hydrofluoric acid."

The problem of controlling the surface temperatures of core vessels in two-region aqueous homogeneous reactors has been examined by analyzing several possible systems for cooling the wall: (1) direction of the inlet core fluid along the wall at a high velocity; (2) passage of heavy water through the wall of a double-wall core vessel; and (3) flow of cool blanket slurry past the wall.

Report presenting the effect of fuel properties on combustion-liner temperatures in a single tubular combustor at combustor-inlet conditions representative of those encountered in turbojet-powered high-flight-speed aircraft. Testing was conducted with three liquid jet-type fuels that varied in voltaility and aromatic content. The variations in fuel properties were found to produce only moderate and not always consistent changes in average liner temperature.

Memorandum presenting the development of fabrication techniques to provide cast-cored turbine blades with hollow tip sections. Two types of modified cast-cored blades that provided an 11-percent weight reduction from a fully cast-cored blade and a 13-percent weight reduction from a standard uncooled blade were investigated in a turbojet engine modified for air-cooling. Results regarding the experimental heat-transfer, temperature comparison with other cooled-blade configurations, calculated and experimental blade temperatures, cooling-air pressure drop, and structural reliability are provided.

From Introduction: "The purpose of this report is to present the results of an analytical investigation of the engine characteristics of two-spool engines with high over-all compressor pressure ratio (12.0 at design). Some of the turbine design problems encountered in a single-spool engine with current compressor pressure ratio (7.32 at design) were investigated in reference 1. The investigation was extended in reference 2 to cover the effect of mode of engine operation on the turbine design requirements and engine performance for a single-spool engine with current compressor pressure ratio."

Report presenting an investigation in the supersonic wind tunnel on a cylindrical-shroud ejector. Data were obtained at several weight-flow ratios, primary pressure ratios, and free-stream Mach numbers. The results indicate that there was no effect of free-stream Mach number on the pumping characteristics of an ejector of this type. Results regarding the internal characteristics and external characteristics are provided.

From Introduction: "The combustor efficiency, combustor total-pressure ratio, combustor-outlet total pressure, combustor-inlet Mach number, and specific fuel consumption are presented. The effect of combustor length on efficiency and the effect of pilot operating conditions burning limits are also presented."

Interaction of convected field of turbulence with shock wave is analyzed to yield modified turbulence, entropy spottiness, and noise generated downstream of the shock. Analysis is generalization of single-spectrum-wave treatment of NACA-TN-2864. Formulas for spectra and correlations are obtained. Numerical calculations yield curves of rms velocity components, temperature, pressure, and noise in db against Mach number for m = 1 to infinity; both isotropic and strongly axisymmetric (lateral/longitudinal = 36/1) initial turbulence are treated. In either case, turbulence of 0.1 percent longitudinal component generates about 120 dbs of noise.

From Summary: "In order to determine the conditions of engine operation causing the most severe thermal stresses in the hot parts of a turbojet engine, a J47-25 engine was instrumented with thermocouples and operated to obtain engine material temperatures under steady-state and transient conditions. Temperatures measured during rated take-off conditions of nozzle guide vanes downstream of a single combustor differed on the order of 400 degrees F depending on the relation of the blades position to the highest temperature zone of the burner. Under the same operation conditions, measured midspan temperatures in a nozzle guide vane in the highest temperature zone of a combustor wake ranged from approximately 1670 degrees F at leading and trailing edges to 1340 degrees F at midchord on the convex side of the blade."

"The effect of correcting quadrupole lenses on the betatron oscillation characteristics of an AG synchrotron was studied, and general formulas are given for the fractional changes of the amplitude and phase functions. Calculations performed for different setups of different numbers of lenses for the CEA synchrotron structure point out that one may correct for sizable errors in the n- value by means of 8 pairs of quadrupole lenses in two consecutive straight sections with the focusing lens between defocusing sectors and vice versa. An increase of BETA /sub max/ of about 5% is obtained for DELTA n/n approximately 0.04. It was found that the necessary corrections can probably be obtained satisfactorily with lenses of 6 in. length. "