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: Authority of the House of Representatives to authorize payment from the Contingent Expense Fund for official telephone calls by members during the year beginning May 28, 1953, in accordance with House Simple Resolution.

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; Several questions relating to the authority of the Board of School Trustees to group, annex, or consolidate a common school district and two independent school districts under the submitted facts.

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; Authority of the Commissioners' Court to permit the movement of overweight, oversize, or overlength equipment on State designated highways.

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;Legality of operations of airplanes by the game and Fish Commission.

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: Authority of the commissioners' court to employ persons to work in each commissioner's precinct rather than allowing each commissioner to select his precinct employees.

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 the same person being paid both as consulting architect and as associate architect in connection with the Basic Science Building for Southwestern Medical School.

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: Maximum compensation and expense allowance of county commissioners of Starr County.

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: Title to real property through purchase at a sheriff's tax sale under the submitted facts.

Abstract: The Happy Jack uranium deposit of White Carron, San Juan County, Utah, was studied in connection with an Atomic Energy Commission exploration program. The major uranium ore control is a paleostream channel containing sediments of the Shinarump conglomerate. Intrachannel controls include organic matter, lithologic variations, and channel "lows". Microscopic studies reveal that uraninite, the primary ore mineral, occurs as cement and as a replacement of organic material. Both the uraninite and copper sulfides replace secondary quartz overgrowths. Crystals of chalcopyrite, chalcocite, and pyrite occur one within the other. Resolution of bornite and chalcopyrite is present. Uraninite is dated as later than the secondary overgrowths and of about the same age as the copper sulfides.

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An analytical investigation was made of two supersonic interceptor type airplanes to determine the most desirable turbojet engine characteristics for this application The airplanes were designed differently primarily because of the amount of subsonic flight incorporated in the flight plan--one flight having none and the other, a cruise radius of 400 nautical miles. Several power plant design variables were varied independently to determine the effect of changes in each parameter on airplane performance. These parameters included compressor pressure ratio, compressor efficiency, turbine-inlet temperature, afterburner temperature, engine specific weight, and air-handling capacity. The effects of using a convergent-divergent exhaust nozzle and of changing the design flight Mach number were also investigated.

Report presenting an investigation to determine the predictability of using ceramals with comparatively low strategic material content for the blades of aircraft turbines, including testing with four different blade root configurations. The most favorable results were obtained for ceramal turbine blades with single serration interlock and dovetail root configurations. Results are also provided for fir-tree blade runs and 4-pin blade runs.

Report presenting a review of the literature pertaining to the use of orthotoluidine and triethylamine in rocket propellant combinations and a summary with particular emphasis on ignition delay investigations and fuel mixture applications. The survey indicated that orthotoluidine is about as good a rocket fuel as aniline with respect to cost, performance, and ignition characteristics, but it has a wider temperature application because of its lower freezing point.

From Introduction: "Because of variation in the static-pressure drop across the porous material and in the cooling air required along the length of afterburner combustion chambers, a prescribed distribution of permeability is usually necessary. However, as a preliminary investigation, this report is concerned only with the attainment of uniform permeability. The results of an experimental investigation, conducted at the NACA Lewis laboratory, to determine the permeabilities of five thick meshes of wire filter cloth are presented herein."

Report presenting an investigation to determine the effect of rate of flap deflection on flap hinge moment and wing lift at a range of Mach and Reynolds numbers. For the rate of flap-deflection range investigated, the hinge-moment coefficient was practically independent of rate of flap deflection.

Report discussing the importance of designing aircraft turbines so that the entire range of operating conditions has been considered. In this particular investigation, the compressor performance was used to determine the turbine design requirements for a turbine-propeller engine to be operated up to altitudes of 40,000 feet and flight velocities up to 600 miles per hour. The two modes of engine operation considered were constant exhaust-nozzle area and variable exhaust-nozzle area.

Report presenting a flight investigation to determine the drag and stability at low lift coefficients of models of a modified-delta-wing airplane at a range of Mach and Reynolds numbers. A summary of the drag and stability data from the tests is provided.

Report presenting an investigation of the effects of heat transfer on boundary-layer transition at higher Reynolds numbers, greater amounts of heating, and a more extensive study of the effects of surface irregularities than what was published in a previous report. Report presenting tests with a smooth model and tests with surface roughness and tunnel flow disturbance are provided.

From Summary: "An experimental investigation of high-frequency combustion oscillations (screaming) was conducted with a 100-pound-thrust acid-hydrocarbon rocket engine and a 500-pound-thrust oxygen-fuel rocket engine. The oscillation frequencies could be correlated as a linear function of the parameter C/L, where C is the experimentally measured characteristic velocity and L is the combustion-chamber length. The tendency of the engines to scream increased as chamber length was increased. With engine configurations that normally had a low efficiency, screaming resulted in increased performance; at the same time, a five to tenfold increase in heat-transfer rate occurred. It was possible, however, to achieve good performance without screaming."

Report presenting a study of the effects of high reactor and cycle temperatures and the effect of thickness of high-temperature fuel element materials on the feasibility of the nuclear-powered direct-air-cycle aircraft for flight at Mach number 1.5 and an altitude of 35,000 feet. Testing occurred over a range of reactor fuel temperatures, turbine-inlet temperatures, and reactor fuel plate thicknesses.

Report presenting an investigation studying the effects of compressibility on the internal-flow characteristics of an NACA 1-series cowling-spinner combination equipped with a dual-rotation propeller at Mach numbers up to 0.8. Two propellers were examined, one with a sealed propeller-spinner juncture and one with a raised-platform-airfoil shaped juncture. The propeller was not found to have appreciable compressibility effects on the impact pressures when operating at design cruise blade angle.

Report presenting testing of four delta-wing and body combinations at specified Mach numbers to determine the effect of oscillation amplitude on the damping in pitch. The body tested was the same, but the wings had 25 degree, 30 degree, 35 degree, and 45 degree semiapex angles. Results indicate that the damping-in-pitch parameter can be predicted by theory, and when a variation of this parameter with amplitude occurs, it is usually small and camping increases with decreasing amplitude.

From Introduction: "In response to the ever-increasing need for high thrust augmentation, an investigation was conducted that had as its primary objective the attainment of maximum exhaust-gas temperature and thrust (ref. 1). The investigation reported herein was therefore conducted to ascertain the operational limits of the most promising high-temperature afterburner design of reference 1 and to determine its performance over a wind range of flight conditions."

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