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, Grover Sellers, regarding a legal question submitted for clarification: Construction of S. B. 338, 49th Leg., in respect to tuition refunds to veterans.

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, Gerald Mann, regarding a legal question submitted for clarification: Whether taxes collected under Texas Rice Development Act, H.B. 136, Acts 47th Leg., may be held in escrow pending judicial determination of validity of the Act.

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: Constitutionality of Art. 924, V.P.C., and related questions concerning oil exploration work in the Gulf of Mexico.

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: Several questions regarding the construction of H.B.158, Acts of the 51st Legislature.

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: Correct method of assessing taxes on royalty interests in a unitized oil and gas production unit which is located in two school districts.

Recent discussions in the group have given rise to the problem of determining whether the beta contamination found in the Columbia River is carried by the algae which are found in the retention basin. The algae accumulate in the basin and apparently remain there longer than the retained water, and thus may be contaminated to a greater extent than the water itself.

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Report presenting an experimental study of the pressure fluctuations at the combustion-chamber inlets of a ramjet operating a Mach number of 1.92 in the supersonic tunnel. Results are presented for two burner configurations of different operating characteristics to indicate trends in pressure magnitude, frequency, and wave form. Results regarding the perforated conical flame holder, regenerative-type burner, and diffuser total-pressure recovery are provided.

Report presenting transonic speed testing utilizing a rocket-powered Bell XS-1 airplane with 10-percent-thick wing and 8-percent-thick horizontal tail. Information is provided for flights up to Mach number 1.06 and altitudes of about 40,000 feet. Results regarding the variation of control-surface positions and forces and sideslip angle with Mach number, time history, rudder effectiveness, and lateral oscillations are provided.

The absolute excitation functions for the production of fission by charged particle bombardment in several substances were investigated at both high and low energies. The low energy work was done at the 60-inch Crocker cyclotron with alpha particles and deuterons, while the high energy work was done at the 184-inch cyclotron with alpha particles, deuterons, and protons.

"Spin tests have been conducted in the Langley free-spinning tunnel on a 1/16-scale model of the McDonnell XP-85 airplane with the normal X-tail replaced with a short-coupled conventional tail arrangement. The effect of the conventional tail arrangement and the effects of various modifications upon the spin and recovery characteristics of the model were determined. The results of the tests indicated that installation of the conventional tail arrangement will not provide satisfactory recoveries from spins of the airplane" (p. 1).

From Summary: "The hottest part of a turbine blade is likely to be the trailing portion. When the blades are cooled and when water is used as the coolant, the cooling passages are placed as close as possible to the trailing edge in order to cool this portion. In some cases, however, the trailing portion of the blade is so narrow, for aerodynamic reasons, that water passages cannot be located very near the trailing edge. Because ceramic coatings offer the possibility of protection for the trailing part of such narrow blades, a theoretical study has been made of the cooling effect of a ceramic coating on: (1) the blade-metal temperature when the gas temperature is unchanged, and (2) the gas temperature when the metal temperature is unchanged."