Report presenting an investigation at transonic speeds to determine the maximum lift characteristics of a wing model of the X-1 airplane. Lift, drag, and pitching-moment data for a lift range and range of Mach numbers was collected. Maximum lift was found to be obtained at progressively higher angles of attack as the Mach number was increased.

The performance of a 16-stage axial-flow compressor, in which the mean-radius solidity was reduced from 1.28 to 1.02 in the fourteenth through sixteenth stage rotors was determined. The performance of this modification was compared with that of the compressor with original rotors. The reduced solidity resulted in slightly improved performance.

Memorandum presenting an investigation of the compressor and turbine operating trends during acceleration and deceleration of two hypothetical two-spool turbojet engines. The two engines have the same component performance maps but the arbitrarily specified ratio of outer- to inner-spool moment of inertia for the second engine is 4 times that specified for the first engine. Results regarding the acceleration characteristics and deceleration characteristics are provided.

The following report covers an investigation that was done to supplement available experimental data on flow fields behind wings of an aircraft at supersonic speeds, as well as to furnish more quantitative information on the choice of the theoretical method for a given configuration and the accuracy to be expected when using such a method.

Report presenting an investigation to determine the effect of outer-shell design variables on the internal performance characteristics of plug-type nozzles designed for a pressure ratio between 6 and 12. Inlet Mach number and outer-shell angle were found to have no effect on nozzle thrust coefficient. For choked flow, the effective throat area decreased when the inlet Mach number or outer-shell angle was increased.

Report presenting an investigation of the boattail pressures and base pressures of two twin-jet afterbody configurations at Mach number 1.91. They were designed as a simple merging of two blunt-based conical afterbodies with spacings of 1.4 and 1.7 jet diameters between the jet center lines. Results regarding support-strut interference, effect of jet spacing ratio, effect of jet exit angle, longitudinal boattail pressure distribution, circumferential pressure distributions, and effect of a reflection plane are provided.

Report presenting an investigation in the 8- by 6-foot supersonic wind tunnel at several free-stream Mach numbers for a range of primary-nozzle pressure ratios and secondary weight-flow ratios to determine the effects on performance of varying the ejector diameter ratio by simulated iris flaps. Results indicated that increases in ejector gross force and secondary-to-primary total-pressure ratio were obtained subsonically when diameter ratio was reduced, thus reducing overexpansion losses.

Report presenting an analysis of losses occurring in a series of subsonic turbine blades in a low-speed two-dimensional cascade and in a related series of four transonic rotors. Results regarding the two-dimensional cascade loss correlations, transonic turbine loss correlations, effect of unsteady flows, and mixing of stator wakes are provided.

Report presenting a review of NACA research on slurry fuels through 1954. Slurry fuels are defined as suspensions of metals in hydrocarbons, which may offer more flight range or thrust than can be obtained with conventional hydrocarbons. Magnesium is the primary metal of interest at this time for high thrust and boron for long-range flight.

Memorandum presenting a free-flight investigation conducted on four supersonic nose inlets. Each inlet used conical-shock and isentropic-compression center bodies; two of the models had internal contraction and two did not. Results regarding drag coefficient, pressure recovery, mass-flow ratio, and Reynolds number range are provided.

Report presenting the wing-section pressure-distribution and wing-panel load characteristics of the Douglas D-558-II airplane for a range of Mach numbers and airplane normal-force coefficients. At subsonic speeds, the pressure distributions are characterized by a high negative-pressure peak with an abrupt pressure recovery as a result of the leading-edge expansion over the upper surface at moderate angles of attack.

Report presenting static lateral- and longitudinal-stability tests of a scale model of a projected, low-aspect-ratio, supersonic airplane at low and high subsonic Mach numbers. The wing was equipped with leading-edge flaps and had a modified double-wedge airfoil with sharp leading and trailing edges. Results regarding lift characteristics, static longitudinal stability and control, lateral and directional stability, drag characteristics, and wing and fuselage tuft studies are provided.

Memorandum presenting the effects of wing modification and stability augmentation on the computed longitudinal behavior in the pitch-up region and probable pilot opinion of the pitch-up characteristics of two current fighter airplanes. An exploration of the addition of a wing-leading edge is included. Results regarding computed pitch-up behavior and probable pilot opinion are provided.

"An analytical solution has been obtained for the equations of motion of water droplets impinging on a wedge in a two-dimensional supersonic flow field with a shock wave attached to the wedge. The closed-form solution yields analytical expressions for the equation of the droplet trajectory, the local rate of impingement and the impingement velocity at any point on the wedge surface, and the total rate of impingement. The analytical expressions are utilized to determine the impingement on the forward surfaces of diamond airfoils in supersonic flow fields with attached shock waves" (p. 85).

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 District Attorney to determine when it is necessary and desirable to appoint a grand jury bailiff and the duty of the commissioners' court to authorize payment for services rendered by a bailiff so appointed.

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; Construction of Senate Bill 74, 54th Legislature, amending Article 1404b, V.P.C.

Report discussing the relative thermal conductivities of liquid lithium, sodium, and eutectic NaK, and the specific heat of liquid lithium, as well as the methods and materials used to determine this information.

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From abstract: This paper presents the results of a study of the error in radio interferometer measurements of near sources attributable to the use of asymptotic formulae, valid for distant targets.

The neocuproine colorimetric method was applied to the determination of copper in yttrium metal. From 5 to 80 - g of copper was determined in the presence of as much as 5OO mg of yttrium with a coefficient of variation of 2%. Copper was reduced to copper (I) with hydroxylamine and complexed with neocuproine (2,9-dimethyl-1,10-phenanthroline). The colored complex was extracted into chloroform and its absorbance measured, after dilution with ethanol, at 457 m - . (auth)

A method for the direct determination of uranium in a cyclohexane solution of tri-n-octylphosphine oxide (TOPO) is presented. The adduct, UO/sub 2/ Cl/sub 2/ x 2TOPO, that is formed when uranium(VI) is extracted from hydrochloric acid solutions by tri-n-octylphosphine oxide absorbs light in the ultraviolet region. This absorbance is measured at 230 m mu vs. a TOPO-cyclohexane solution that was contacted with hydrochloric acid of the same concentration as that in the test aliquot. The molar absorbance index is 5500. The method is not selective; of the elements that are extracted by TOPO from hydrochloric acid, iron(III), zirconium, molybdenum, tin and thorium, only thorium can be tolerated. (auth)

Eleven thorium-carbon alloys in the range 0.02 to 2.0% carbon were prepared by vacuum-arc melting. The hardness varied from 19 R/sub A/ for the 0.02% alloy to 108 R/sub B/ for the 2.0% alloy. The preparation of thorium- chromium alloy was hampered by a reaction with the zirconia molds, which results in porosity in the casting. The failure of aluminum-silicon bonded X-10 slugs after heat treatment for seven days at 400 deg C was traced to the failure to remove tin after the tin dip and the presence of a gas during heat treatment. Tensile tests were made on extruded thorium, and no correlation was found with extrusion variables. A composition effect was found, however, which showed a linear relationship between carbon content and tensile strength. Creep tests on thorium, uranium, and Inconel continue. The program of evaluating the variables in the fabrication of clad fuel elements, using MTR techniques was concerned mainly with the distribution of UO/sub 2/ in the core compact, the temperature of rolling, and the particle size of the metallic core powder. Progress is being made in the preparation of three-layer laminates without the use of a protective can during the hot-rolling operation but with the …

A brief survey of decarboxylation reactions and carboxylation reactions that are known or presumed in biological systems will be presented. While a considerable number of amino acid decarboxylations are known, their mechanisms will not be included in the present discussion but will be reserved for a later paper in the symposium. The remaining decarboxylation reactions may be subdivided into oxidative and nonoxidative decarboxylations. In most cases, these reactions are practically irreversible except when coupled with suitable energy-yielding systems. The carboxylation reactions which are useful in the formation of carbon-carbon bonds in biological systems seem to fall into two or three groups: those which exhibit an apparent ATP requirement, and those which exhibit a reduced pyridine nucleotide requirement, and those which exhibit no apparent ATP requirement. Of the first group at least four cases, and possibly six or seven, are known, and one interpretation of them involves the preliminary formation of 'active' carbon dioxide, generally in the form of a carbonic acid-phosphoric acid anhydride. Those exhibiting no apparent ATP requirement seem to be susceptible to classifications as enol carboxylations in which the energy level of the substrate compound is high, rather than that of the carbon dioxide. There appear to be …

Uranium dioxide pellets sealed in Type 316 stainless steel containers with a helium gas were irradiated in helium and in C0/sub 2/ in thermal fluxes or the order of 1 x 10/sup 13/ n/(cm/sup 2/)(sec). Cladding-surface temperatures were reportedly between 1200 and about 1800 F. The hot-cell examination performed by BMI showed that there were no obvious effects of the irradiation on the specimen tested in helium. However, the specimen irradiated in the presence of C0/sub 2/ exhibited severe cladding-CO/sub 2/ reaction and possible central melting of the UO/sub 2/. Although comparisons between pre- and postirradiation data were difficult because of involved fabrication history of the specimens, the tests did further establish the fact that helium is a satisfactory coolant gas for stainless steel cladding material at a temperature of 1200 F. The data obtained from the specimen tested in the presence of C0/sub 2/ indicate that at temperatures in the range of 1600 to 1800 F Type 316 stainless steel is not compatible with C0/sub 2/. (auth)