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: Use of assessed property value in computation of the franchise tax.

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: Exemption from State and county ad valorem taxes of residence of Assistant Rector.

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: Inheritance tax liability of bequests to certain foreign charitable corporations.

Memorandum presenting an experimental investigation of various methods for the control of afterburner combustion screech at afterburner-inlet total pressures from 4000 to 6400 pounds per square foot absolute. Generally, the range of afterburner fuel-air ratios in which screech occurred and the intensity of screech did not vary appreciably in the range of pressures covered.

Report presenting a discussion of the use of an effective rotor-blade momentum thickness in describing rotor-blade loss characteristics. A derivation of the necessary equations is presented for obtaining momentum thickness for given overall turbine performance, stator performance, and rotor geometric quantities.

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It was shown that without further major development the detectors proposed for the Body Monitor can be expected to detect 0.02 microcurie of plutonium at the center of the chest cavity. This is the permissible body burden of insoluble forms of plutonium. The detection level can be decreased by decreasing the background counting rate. Decreases in the background can reasonably be expected; it should be possible to detect a small fraction of the permissible body burden. If it can be shown, as suggested by other work, that americium will remain with plutonium, then within at least a few months after entry into the body it should be possible to measure the plutonium by detection of rays from Am²⁴¹.

The purpose of this report is to provide data pertaining to the corrosion damage incurred in the use of oxalic acid as a cleaning agent for process equipment.

Report presenting testing of a series of single and double unswept, lateral-support struts at a Mach number of 1.9 on a cone-cylinder body at zero angle of attack. The struts consisted of a rectangular box section with identical wedge fairings fore and aft. Results regarding the shock-wave intersections and pressure distributions are provided.

From Summary: "Heating requirements for satisfactory cyclic de-icing over a wide range of icing and operating conditions have been determined for a gas-heated, 36 degree swept airfoil of 6.9-foot chord with a partial-span leading-edge slat. Comparisons of heating requirements and effectiveness were made between the slatted and unslatted portions of the airfoil. Studies were also made comparing cyclic de-icing with continuous anti-icing, and cyclic de-icing systems with and without leading-edge ice-free parting strips. De-icing heat requirements were approximately the same with either heated or unheated parting strips because of the aerodynamic effects of the 36 degrees sweep angle and the spanwise saw-tooth profile of leading-edge glaze-ice deposits. Cyclic de-icing heat-source requirements were found to be one-fourth or less of the heat requirements for complete anti-icing. The primary factors that affected the performance of the cyclic de-icing heating system were ambient air temperature, heat distribution, and thermal lag."

Report presenting gas-to-blade heat-transfer coefficients and turbine heat-rejection rates obtained for a wide range of one-spool turbojet engine designs believed to be representative of engines that will employ turbine cooling. The values of heat-transfer coefficient and heat-rejection rates are applicable to both liquid- and air-cooled turbines. Results regarding the heat-transfer coefficients and heat-rejection rates for turbojet engine designs, total heat-rejection rates for various turbojet engine and flight conditions, and heat-transfer coefficients and heat-rejection rates for turboprop engine design are provided.