Abstract: "A simple solution to Saha's equation has been obtained. The method of solution involves iteration with respect to the electron pressure or concentration and can be applied to the simultaneous calculations of any number of ions. Sample results are given for lithium and aluminum."

Memorandum presenting flight tests conducted on two straight-wing jet airplanes of generally similar configuration, one exhibiting a diving tendency and the other a climbing tendency, in order to investigate the cause for the particular type of behavior of each airplane at high Mach numbers. The results showed that the diving tendency experienced by the one airplane was due to the predominant effect of an increased angle of attack of the horizontal tail.

From Introduction: "Results presented herein show the altitude performance of the turbine-propeller engine and its components and the applicability of the generalization method for predicting engine and component performance at altitudes other than the test altitude. Data from a brief investigation of windmilling and altitude starting characteristics of the engine also presented."

From Introduction: "The engine evaluation of blends reported herein was conducted at the NACA Lewis laboratory. The data contained in references 2 to 14 are therefore summarized and the effect of the molecular structure of fuels on antiknock performance is shown in herein."

Report presenting the results of a wind-tunnel investigation to determine the control effectiveness and variations of forces and moments as functions of angles of attack and sideslip for a scale model of the MX-775A missile at a range of Mach and Reynolds numbers. Results regarding the static longitudinal stability and control characteristics, Reynolds number effects, lateral-control characteristics, and clipped-wing configuration characteristics are provided.

"An investigation of the performance of a 16-inch ram jet engine having a single oblique-shock all-external compression inlet designed for a flight Mach number of 1.8, was conducted in the NACA Lewis 8-by 6-foot supersonic wind tunnel. Data were obtained at Mach numbers from 1.5 to 2.0 and angles of attack from 0 degrees to 10 degrees. Three exit nozzles were used; a cylindrical extension of the combustion chamber, a 4 degrees half-angle converging nozzle with a 0.71 contraction ratio, and a graphite converging-diverging nozzle having a 0.71 contraction ratio plus reexpansion to essentially major body diameter" (p. 1).

"During the course of an investigation by the Langley Pilotless Aircraft Research Division regarding the effectiveness of spoilers and ailerons on sweptback tapered wings, it was necessary to test a given control configuration on wings of varying degrees of stiffness. In the process of conducting these tests, repeated wing failure was experienced with the weaker wing-spoiler configurations, whereas no failure occurred with any of the wing-aileron models. An investigation which was conducted by means of rocket-propelled test vehicles in free flight showed that the cause of the repeated failures was flutter of the bending-torsion type" (p. 1).

From Introduction: "The ram-jet missile studied in the present report is one type of shieldless which has the advantage of employing the simplest type of propulsion system."

Report presenting an analysis of the blade-element performance of a highly loaded transonic rotor with double-circular-arc blades. The rotor was purposely loaded beyond the prudent level for exploratory purposes. Results regarding the radial-distribution plots, blade-element data, element blade-to-blade loss variation, and a comparison of steady-state and hot-wire measurements are provided.

Report presenting a wind tunnel investigation to determine the effects of a blowing type boundary-layer control flap on the longitudinal control and lateral stability and control of an F-86D airplane. Tests were made using the following lateral control devices: split-flap-type spoilers, differentially deflected flaps, and differential amounts of blowing over the flaps.

Report presenting calculations by the method of characteristics of 2960 boundaries of supersonic axisymmetric free jets exhausting from conically divergent nozzles into still air. The calculations covered a range of jet Mach numbers, a ratio of specific heats of the jet, divergence angles of the nozzle, and jet static-pressure ratios. Results regarding the effect of increasing the static pressure ratio, the simulation of one jet boundary by another, and interpolation and extrapolation of calculated boundaries are provided.

Memorandum presenting a survey and evaluation of flutter research and flutter engineering, with particular emphasis placed on the design of primary fixed surfaces and primary controls. Analyses are made of recent flutter occurrences to delineate past and future problems, and detailed appraisals are given of the status of the various engineering branches involved in the analytical and experimental prediction of flutter.

"As part of the Navy Project Zip to consider various boron-containing materials as possible high-energy fuels, the chemical and physical properties of Hi-Cal-2 prepared by the Callery Chemical Company were evaluated at the NACA Lewis laboratory. Elemental chemical analysis, heat of combustion, vapor pressure and decomposition, freezing point, density, self ignition temperature, flash point, and blow-out velocity were determined for the fuel. Although the precision of measurement of these properties was not equal to that obtained for hydrocarbons, this special release research memorandum was prepared to make the data available as soon as possible" (p. 1).

Performance data and characteristics of a 16-inch impulse-type supersonic-compressor rotor are presented. The experimental portion of this investigation was conducted in Freon-12. A peak pressure ratio of 3.6 was obtained with an adiabatic efficiency of 0.80 at design conditions. Performance was continuous from impulse operation, at open throttle, to shock-in-rotor operation at the stall condition.

"Dynamic--response measurements for various conditions of displacement and rate signal input, sensitivity setting, and simulated hinge moment were made of the three control-surface servo systems of an NAES-equipped remote-controlled airplane while on the ground. The basic components of the servo systems are those of the General Electric Company type G-1 autopilot using electrical signal sources, solenoid-operated valves, and hydraulic pistons. The test procedures and difficulties are discussed" (p. 1).

Ignition delays of a diallylaniline-triethylamine mixture and of triethyl trithioposphite with red fuming nitric acid were measured as a function of combustor dimensions, initial propellant temperature, and initial ambient pressure. Ignition delay increased with exhaust-nozzle diameter. Ignition delay also increased as propellant temperature decreased, but did not vary with initial ambient pressure except with the largest nozzle diameter. A correlation among ignition delay, combustor dimensions, and propellant temperature is presented, and the extension of the correlation to other systems is discussed.

Discussing an examination made of uranium deposits on the southwest rim of the Lukachukai Mountains, in Northeast Arizona

Leaching investigations on low grade Belgian Congo uranium ores and recovery of uranium from acid leach solutions by uranous phosphate precipitation, uranyl phosphate precipitation and by sodium carbonate retreatment of alkali precipitates are described.

This document presents a set of machine-computed curves involving a wide range of Kb and Kc, from which both thermal and resonance values of (E-1) may be obtained.