Report issued by the Bureau of Mines over investigations of coking coal reserves of Scott County, Tennessee. Testing to determine suitability for producing metallurgical coke is also presented. This report includes tables, maps, and illustrations.

Report issued by the Bureau of Mines over investigations of coking-coal reserves of Monongalia County, West Virginia. Methods used, and measurements of coal reserves are listed. This report includes tables, and maps.

Report issued by the Bureau of Mines over investigations of coking-coal reserves of Bledsoe County, Tennessee. Methods used, and measurements of coal reserves are listed. This report includes tables, and maps.

Report issued by the Bureau of Mines over investigations of coking coal reserves of Fentress County, Tennessee. Testing to determine suitability for producing metallurgical coke is also presented. This report includes tables, maps, and illustrations.

Abstract: "The heat-treatment behavior of zirconium alloys containing 7 to 70 w/o uranium is described. The effect of oxygen contamination on the structure and hardness of these alloys is outlined. It is shown that in the initial stages pf transformation of beta zirconium-uranium solid solution into the low-temperature phases a potent hardening reaction occurs in alloys containing 20 to 70 w/o uranium. In this reaction the hardness may rise from 200 DPH characteristic of retained beta to values in excess of 400 DPH. Practical heat treatments have been developed which produce relatively soft alloys. The microstructures and hardnesses produces by these treatments are shown."

Abstract: The thermal distortion of a Y-shaped hafnium control rod heated by arrays of individually controlled radiation heaters was studied. The large axial and radial temperature gradients specified for this control rod were easily obtained with the radiation-heating method. The distortion, as measured with dial indicators, amounted to a 2-mil movement of the free end of the rod in the direction of the coolest blade.

Abstract: "Approximate melting points have been determined for five samples of uranium tetrafluoride representing incompletely converted uranium dioxide and covering the range from about 2 to 20 w/o UO2, using the method of differential thermal analysis. The results indicate the melting temperatures are in the range of 920 to 980 C. No significant correlation between melting point and UO2 content was observed, possibly because of calcite formation. Similar results were obtained on synthetic mistakes of UF4 containing from 10 to 40 w/o UO2."

"Characteristics of a pulsed, occluded-gas ion source, operating in a magnetic field, have been investigated. Mass spectra of hydrogen- and deuterium-loaded sources are presented. Constructional details of the source and its operating characteristics are discussed."

Abstract: "This report describes six electronics areas at the Radiation Laboratory (Berkeley and Livermore) that are being successfully used with various particle acceleration for nuclear research. The electronics equipment, consisting of pulse amplifiers, scalers, coincidence circuits, pulse-height analyzers, automatic recording equipment, high-voltage supplies, etc., is arranged in such a manner that most experiments can be quickly set up, and a number of people can run experiments simultaneously. Advantage and limitations of these areas are discussed."

Report presenting an investigation of the lateral stability and control effectiveness of a model of a fighter-type airplane model with a low-aspect-ratio and 3.4-percent-thick wing with negative dihedral at a range of Mach numbers, sideslip angles, and angles of attack. Results regarding the lateral characteristics at zero angle of attack, lifting conditions, and lateral and directional controls are provided.

Memorandum presenting an annotated bibliography of NACA reports containing information of interest to designers and manufacturers of controls for turbojet engines. The eleven major topics include starting, acceleration, flame-out, temperature control, stability and dynamics of small disturbances, combustion dynamics, engine inlet diffuser control, steady-state engine performance, fuel systems, sensors, and general control system theory.

Research conducted at the NACA Lewis Laboratory on ignition of flowing gases by means of long-duration discharges is summarized and analyzed. Data showing the effect of a flowing combustible mixture on the physical and electrical characteristics of spark discharges and data showing the effects of variables on the spark energy required for ignition that has been developed to predict the effect of many of the gas-stream and spark variables is described and applied to a limited amount of experimental data.

Memorandum presenting an investigation of a full-scale afterburner with high burner-inlet velocity conducted to determine burner performance with several variations in burner design. Variables receiving particular attention were flameholder design and burner length. Results regarding diffuser performance, performance of the reference two-V-gutter flameholder, designs to improve combustion for high-velocity conditions, and operational characteristics are provided.

Memorandum presenting an investigation to determine the roll effectiveness of a differentially deflected horizontal tail of a 42 degree swept-wing model. The model was tested through an angle-of-attack range of 0 degrees through the stall in the clean and landing configurations with the horizontal tail in a low position. Results regarding the longitudinal characteristics and lateral characteristics are provided.

Report presenting an investigation on a transonic bump to determine the aerodynamic characteristics of a series of triangular wings. Four basic triangular-wing plan forms with different aspect ratios, taper ratios, and combinations of tip clipping were tested over a range of Mach and Reynolds numbers. Results regarding angle of attack, drag coefficient, pitching-moment coefficient with lift coefficient, and various curves are provided.

Note presenting general equations for the linear responses of inner- and outer-spool speed to change in turbine-inlet temperature and exhaust-nozzle area are derived and evaluated from hypothetical two-spool-engine characteristics at design speed. Experimental corroboration of analysis is also provided in the form of response to fuel flow, response to exhaust-nozzle area, and response to turbine-inlet temperature are provided.

Report presenting the results of flight tests with several typical light aircraft. Flight tests were made with one airplane with two different horizontal tail configurations in an attempt to provide an arrangement that would give optimum conditions with regard to the effect of power change on longitudinal trim near the stall. The results are intended to provide quantitative flight-test information which may be useful to designers in attempting to provide for adequate low-speed control and which may be correlated with analytical analyses.

Note presenting some analytical means by which designers may estimate the elevator deflection required to trim in steady longitudinal flight and to demonstrate in a quantitative manner the effects on longitudinal trim of changes in some of the more important design parameters. The procedures can result in a design in which the maximum up-elevator deflection can be maintained within the highest value that will result in satisfactory damping in roll and reliable lateral control under all flight conditions, while, at the same time, adequate longitudinal control is available.

Note presenting measurements of space heating rate, which can yield information that is useful in characterizing turbulent combustion. For Bunsen burner flames stabilized over a field of pipe-induced turbulence, the space heating rate decreased with increasing linear flow and burner diameter and was independent of pilot conditions. Results regarding residual heat values, space conversion rate, turbulent burning velocities, and a comparison of concepts are provided.

Report presenting an investigation to determine the effect of type and location of impact damage on the fatigue strength of jet-engine compressor blades. The most serious damage was found in the nicks at the leading and trailing edges in the vicinity of the maximum-vibratory-stress section of the airfoil. Results regarding stress distribution in the blades, fatigue of the damaged blades, the fatigue test results, the correlation of reduction in strength, an analysis of the results, and testing using reworked blades are provided.

Report presenting an analysis of temperatures and thermal stresses in typical skin-stiffener combinations of winglike structures subjected to aerodynamic heating using an electronic differential analyzer. Variations were made in aerodynamic heat-transfer parameter, in a joint conductivity parameter, and in the ratio of skin width to skin thickness. Results regarding data obtained,an illustrative example, temperature and stress ratios, and peak stress ratios and temperature-ratio drop across joint are provided.

Report presenting a method for obtaining a power spectrum of gust vertical velocity over a wide range of wavelengths from simultaneous measurements in flight. It has the advantage of not involving the use of airplane transfer functions. Results regarding the measurements of velocity, including long-period and short-period measurements, and a composite spectrum over the range of frequencies are provided.

"Tests utilizing the schileren method of flow photography have been conducted to provide a comparison of the complete flow fields past an unswept- and a swept-wing-body combination and the flow fields past their equivalent bodies of revolution at Mach numbers around 1.0. The results indicated that the shock growth and positions on the wing-body combinations were closely reproduced in the flow past the equivalent body" (p. 1).

Report presenting an investigation in the 300 mph 7- by 10-foot tunnel and gust tunnel to determine the static longitudinal aerodynamic characteristics an the gust-alleviation capabilities of forward-located fixed spoilers, deflectors, or a spoiler-deflector combination on a simulated transport airplane model with an unswept wing. Results regarding the static/force test, dynamic/gust-tunnel test, and short-period frequency and damping are provided.