"The performance and operational characteristics of two afterburner configurations for the Iroquois turbojet engine were evaluated in an altitude test chamber over a range of afterburner equivalence ratios at afterburner-inlet pressures from 733 to 3186 pounds per square foot absolute. These conditions correspond to an altitude range from 38,700 to 66,800 feet at a flight Mach number of 1.5. The only difference between the two afterburner configurations was in the pattern of afterburner fuel injection. At an afterburner-inlet pressure of approximately 3100 pounds per square foot absolute, corresponding to an altitude of 38,700 feet and a flight Mach number of 1.5, the combustion efficiency of both configurations reached peak values of 0.80 to 0.85 at equivalence ratios of 0.35 to 0.40" (p. 1).

Report presenting tests of the extent of laminar flow that can be obtained with practical wing-surface conditions. Chemical sublimation was used for boundary-layer-flow visualization on the wings of a supersonic fighter airplane in level flight. A method of continuous monitoring using heat temperature resistance gauges was also used on one wing.

Chemical sublimation has been employed for boundary-layer-flow visualization on the wings of a supersonic fighter airplane in level flight at speeds near a Mach number of 2.0. The tests have shown that laminar flow can be obtained over extensive areas of the wing with practical wing-surface conditions. In addition to the flow visualization tests, a method of continuously monitoring the conditions of the boundary layer has been applied to flight testing, using heated temperature resistance gages installed in a Fiberglas "glove" installation on one wing. Tests were conducted at speeds from a Mach number of 1.2 to a Mach number of 2.0, at altitudes from 35,000 feet to 56,000 feet. Data obtained at all angles of attack, from near 0 deg to near 10 deg, have shown that the maximum transition Reynolds number on the upper surface of the wing varies from about 2.5 x 10(exp 6) at a Mach number of 1.2 to about 4 x 10(exp 6) at a Mach number of 2.0. On the lower surface, the maximum transition Reynolds number varies from about 2 x 10(exp 6) at a Mach number of 1.2 to about 8 x 10(exp 6) at a Mach number of 2.0.

Report presenting characteristic exhaust-velocity measurements made of the JP-4 fuel-red fuming nitric acid propellant combination in 40-pound-thrust rocket engines with various combustion-chamber lengths and diameters. The results are compared to those from previous studies and discussed in terms of a vaporization model of combustion. Results regarding the effect of UDMH, effect of water on performance of hydrocarbon fuels, effect of water on performance of hydrazine fuel, and some of the chemical and physical factors affecting combustion are provided.

Typical results are given from a calculation of the deposition of heat in stratified lead and water slabs caused by a monodirectional, monoenergetic beam of gamma rays incident on the slabs. A total of 512 cases were calculated for infinite slabs with finite thicknesses of 1, 2, 4, and 6 mean free paths; source energies of 1, 3, 8, and 10 Mev, and source angles of incidence which were chosen to give slant slab thicknesses of 1, 2, 3, and 4 times the normal thickness. The results were fitted to an empirical formula, which can be simplified for special cases. While for the cases examined, the fit was usually good to within 5%, it is to be emphasized that the formula has been compared only with the results from a very limited number of parameters. (auth)

Report presenting the performance of three injector types in a 2400-pound-thrust rocket test chamber. Characteristic velocity and specific impulses were obtained over a range of oxidant-to-fuel ratios at a nominal chamber pressure of 600 pounds per square inch absolute. RMI-1 and 2 had fairly similar results, but RMI-3 gave no stabilized data due to combustion instability.

"Operation of the original engine configuration disclosed a severe compressor stall problem at high altitude, which was largely attributed to a radial flow distortion entering the high-pressure compressor. Engine modifications for eliminating or alleviating the stall problem were investigated. These included use of variable high-pressure compressor inlet guide vanes, increased turbine-stator areas, and minor alterations in both the low- and high-pressure compressor rotors" (Abstract).

Results regarding testing of steel projectiles fired into copper targets at velocities from 5,000 to 11,500 feet per second, which indicated that as target temperature is increased, the crater size also increases. Twenty-two caliber steel cylinders and steel spheres were used as projectiles.

Results regarding testing of steel projectiles fired into copper targets at velocities from 5,000 to 11,500 feet per second, which indicated that as target temperature is increased, the crater size also increases. Twenty-two caliber steel cylinders and steel spheres were used as projectiles.

The partial differential equations of the multigroup diffusion model of reactor physics are shown to have solutions both in the time-independent and timedependent problems, and the usually assumed behavior of these solutions is shown to be mathematically valid. The method of spectral representation is developed for the multigroup diffusion operator. (auth)

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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: Proper interpretation to be placed on Sub-section 2 of Section 2a of Article 7047b relating to the amount of taxes to be paid on gas where the seller has an escalator clause in their contract - when the final decision of the Federal Power Commission is pending.

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: Questions concerning per diem and travel allowances for employees of General Land Office - Sections 29, 30, and 31 of House Bill No. 133, Acts of the 55th Legislature, Regular Session, 1957.

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: Whether Comptroller can approve motor fuel tax refund claim form signed in blank by claimant and later filled in by notary public with executed jurat, and whether notary's act in filling in the form and executing the jurat constitutes a felony within the provisions of Section 27(m), Article 7065b, V.C.S.

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: Proper classification for inheritance tax purposes of illegitimate son of deceased brother of decedent.

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: Whether Article 7880-74a or Articles 3937 and 3939 controls the amount of compensation the Williamson County Tax Assessor-Collector is to receive for assessing and collecting taxes for Brushy Creek Water Control and Improvement District Number 1 of Williamson and Milam Counties on property located in such district in Williamson County.