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, Price Daniel, regarding a legal question submitted for clarification: Issuance of revenue bonds under Article 2603c.

From Introduction: "Tests have recently been conducted in the Langley 8-foot high-speed tunnel (reference 1) to study the effects of changes in operating advance ratio, blade plan form, blade-section thickness, section camber, and other variables on the on the propeller characteristics in the transonic-speed range. The method in reference 2, which evaluated the profile drag losses and the induced losses seperately, is followed in this paper. The method as presented offers the general prediction of propeller performance, and can be used to supplement the experimental data."

Report presenting a blade-vibration survey that was conducted during normal operation of a 10-stage axial-flow compressor powered by part of a complete jet engine. Strain-gage records were obtained from all stages during acceleration, deceleration, and constant-speed runs. Results regarding the inlet disturbances and damping characteristics are provided.

A study of the design of the DR Water Plant made for the purpose of estimating the feasibility of effecting an expansion of capacity has shown the following: (1) The Charles T. Main Company design has incorporated spare spaces and other provisions to permit a relatively simple increase in capacity to 42,000 GPM without undue additional design or procurement being required. (2) An increase in capacity to 44,000 GPM would require considerable re-design of the 183-DR, 190-DR and interconnecting pipe lines and would incur costs which may be out of proportion to the small increase in flow attained. In view of the urgency for the completion of the design and construction of this Water Plant, further consideration of an expansion to 44,000 GPM is not recommended.

Report on the atomic bomb injuries in Hiroshima City.

Report presenting an investigation of the time lag between flap deflection and force development on a rectangular wing with a 9-percent-thick symmetrical circular-arc profile with a full-span 30-percent-chord flap. This was performed in order to determine further information about the rapidity of response for a supersonic missile after a given flap deflection due to the potential time lag between the deflection of the controls surfaces and the development of aerodynamic forces.

Memorandum presenting pressure-distribution and force data at various angles of attack of a triangular wing of aspect ratio 2 and having an NACA 0005 modified section. The wing had a plain, constant-chord, trailing-edge flap which was deflected 0 and 10 degrees. Results regarding the gross force characteristics of the wing, including lift, drag, pitching-moment, and flap hinge-moment coefficients are provided.

Report discussing the progress made on the Experimental Breeder Project during the period from March 1, 1949 to January 31, 1950.

Report discussing a procedure for the preparation of anhydrous vanadium trifluoride. From abstract: "By selecting proper operating conditions and equipment, a method of preparation was devised such that anhydrous vanadium trifluoride of high purity was produced reliably in five pound batches." The method of preparation involves manipulating the starting material, vanadium pentoxide.

Report presenting an investigation of thrust augmentation by injection of water and water-alcohol mixtures in the combustion chambers at sea-level zero-ram flight conditions on 4000-pound-thrust axial-flow and centrifugal-flow turbojet engines. Thrust augmentation, compressor characteristics, fuel flow, and turbine-outlet-temperature distributions are presented for various injection rates and water-alcohol mixtures.

A method is presented for analysis of the compressible flow between the hub and the shroud of mixed-flow impellers of arbitrary design. Axial symmetry was assumed, but the forces in the meridional (hub to shroud) plane, which are derived from tangential pressure gradients, were taken into account. The method was applied to an experimental mixed-flow impeller. The analysis of the flow in the meridional plane of the impeller showed that the rotational forces, the blade curvature, and the hub-shroud profile can introduce severe velocity gradients along the hub and the shroud surfaces. Choked flow at the impeller inlet as determined by the analysis was verified by experimental results.

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, Price Daniel, regarding a legal question submitted for clarification: The validity of a contract for revaluation of property within Grand Prairie Independent School District, in reconsideration of Opinion No. V-966.

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, Price Daniel, regarding a legal question submitted for clarification: The extent of the present term of the District Judge, 128th Judicial District, in view of the recent change of this court from a temporary to a permanent status.

Report presenting additional wind-tunnel tests of a model of the X-3 airplane at low and high subsonic numbers to investigate the lateral and longitudinal-stability and control characteristics. Results regarding the aerodynamic characteristics in pitch and aerodynamic characteristics in yaw are provided.

From abstract: This paper presents temperature-entropy and Mollier charts for sodium, and describes briefly the method used for their construction, based upon data from the literature.

Report presenting results obtained with quiescent fuel-air mixtures and with small diffusion flames, which indicate that combustion efficiencies close to 100 percent were obtained at pressure much lower than those found in turbojet combustors at altitudes of 60,000 feet.

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To determine effect of nonuniform inlet-air velocities, a full scale, axial-flow turbojet engine was investigated in Lewis altitude wind tunnel at altitudes from 20,000 to 50,000 feet, 0.21 flight Mach number and corrected engine speeds from 77.3 percent of rated speed to rated speed. Total-pressure variations as large as 103 pounds per square foot in radial direction and 90 pounds per square foot in circumferential direction at 30,000 feet were obtained. With the distortions investigated, net thrust varied between 0.95 and 1.03 of the thrust with uniform inlet-air distribution. Similarly the ratio of specific fuel consumption varied from 1.00 to 1.04. Within the arrange of this investigation the effects of nonuniform inlet velocity were not serious for the engine investigated.

Report presenting the use of porous-walled tunnels at supersonic Mach numbers as a means of avoiding reflection of a stream disturbance extending to the walls. Results from analysis and an experiment with a 4 degree wedge at a Mach number of 1.2 are provided.

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The tests described in this report were static tests devised to afford a basis for a quick evaluation of the resistance of uranium to attack by lithium. The work was done at the same time as the tests of beryllium, thorium, and various engineering metals in lithium (described in ANL-4990); but the results with uranium are given in the present classified report so that the results of the other tests can be published as an unclassified document. The procedure for carrying out the tests is described in ANL-4990.

Ignition characteristics of AN-F-32 and two AN-F-58a fuels were studied in a single can-type turbojet combustor under air-flow conditions representing engine speeds of 1600, 2500, and 4000 rpm, altitudes from sea level to 30,000 feet, ambient temperatures at sea level from 90 degrees to minus 36 degrees F, and flight Mach numbers of 0 and 0.6. Critical fuel-flow rates for ignition increased with increase in preignition engine speed, with increase in altitude, or with decrease in sea-level ambient temperature. This flow rate appears to increase in a direct relation to decrease in fuel volatility as indicated by the 10-percent-evaporated temperature.

A preliminary study was made of the feasibility of three cycles for nuclear propulsion of aircraft: a direct-air-turbojet, a binary liquid-metal turbojet, and a helium compressor jet. All three cycles appeared feasible for flight at a Mach number of 0.9 and altitudes up to 50,000 feet; the liquid-metal cycle appeared feasible for flight at a Mach number of 1.5. The air and helium cycles resulted in heavier aircraft than did the liquid-metal cycle, particularly at a Mach number of 1.5. The relative advantage of the liquid-metal cycle became greater as the flight speed and altitude increased, and as the reactor wall temperature decreased.

Report discussing an investigation into the ability of human pilots to control short-period yawing oscillations using a yaw simulating device. The ability to control the oscillations was determined to be a function of period, control effectiveness, and inherent damping. Pilot control effectiveness was found to improve with practice.