Report presenting a study of the flight characteristics of the canard configuration at transonic and supersonic speeds. Known problems concerning the low-speed characteristics of the canard are also investigated.

Partial abstract: "The investigation of the high temperature and pressure dissociation of water under irradiation was undertaken by the Power Pile Division of Oak Ridge National Laboratory in an effort to determine the degree of importance of the phenomenon with respect to the design of a high temperature water-cooled power reactor. Theory and past experimentation indicate that net steady-state dissociation is determined by the rates of the dissociation and recombination reactions under the imposed conditions, the dissociation rate being essentially a function of flux and the recombination rate essentially a function of temperature" (p. 3).

Abstract: A summary of thermodynamic calculations for zirconium halides is given. Data indicates that the iodide is the most promising of the halides for arc dissociation and that good recoveries of zirconium should be obtainable provided dissociation is carried out at reduced pressure.

Abstract: "Small amounts of acetic acid, equivalent to 400 ul. of 0.3 to 0.13 g/L. can be titrated coulonatrically in the presence of a 10 to 25-fold excess of HN03 in 70%, isopropanol. An accuracy of +/- 0.1% and a precision of +/- 8.5% (99% limite) are obtained.

A vane-type angle-of-attack indicator suitable for measurements at both subsonic and supersonic speeds has been developed by the National Advisory Committee for Aeronautics. A brief history is given of the development, and a wind-tunnel calibration of the indicator is presented, together with a discussion of the corrections to be applied to the indicated readings.

Measurements are presented at Mach numbers from about 1.3 to 1.5 of reflection characteristics and the relative upstream influence of shock waves impinging on a flat surface with both laminar and turbulent boundary layers. The difference between impulse and step waves is discussed and their interaction with the boundary layer is compared. General considerations on the experimental production of shock waves from wedges and cones and examples of reflection of shock waves from supersonic shear layers are also presented.

Memorandum presenting an exploratory investigation to determine the aerodynamic effects of camber on a 60 degree apex delta-wing model conducted in the 300 mph 7- by 10-foot tunnel. Camber variation was accomplished through the deflection of full-span round and 25 degree beveled leading-edge flaps on a flat-sided triangular plan-form wing.

The flux standard is a device which will give a known flux-linkage change to be used as a calibration. At the Radiation Laboratory, two types of flux standards are used, a stationary type and a portable type.

Abstract: "A new method of determining 8-hydroxyquinoline by titration with electrolytucally-generated bromine has been developed. Results show good precision in the range 0.4 mg. to 1.6 mg. total 8-hydroxyquinoline, with 99% confidence limits of less than +/- 2%. An electronically-regulated constant current source, required by the method, is described. A new indicator system with high sensitivity to free bromine is discussed."

From introduction: "This is the first report on the study made of the possible power recovery without excessive cost, from the operation of the Brookhaven reactor."

Report presenting the results of an analytical investigation, which demonstrated that the inlet of a turbojet engine can be protected from ice accretions by bleeding hot gases from other locations within the engine to the inlet without undue loss in thrust. Results regarding the bleedback requirements, engine performance, effect of nozzle area, mixing efficiency, and seriousness of thrust losses are provided.

An investigation on various can-type burners in a Bumblebee 18-inch ram jet under controlled conditions of pressure altitude and ram pressure ratio was conducted in the NACA Lewis altitude wind tunnel with kerosene as fuel. The performance of the following can-type burner configurations was better than that of the other burner configurations investigated: (1) a flame holder having a two-pitch alinement of perforations, 0.07-inch-wide cooling slots, and an arrangement of fuel nozzles located within an annulus having a mean radius of 7.24 inches; and (2) a flame holder having a zero-pitch alinement of perforations, 0.16-inch-wide cooling slots, and an annulus of fuel nozzles having a mean radius of 6.89 inches.

Abstract: "The analysis of hafnium and zirconium by the copper spark technique is presented for solutions of HCl, HF, and HClO4 acids. The special techniques of electrode protection and vacuum drying of perchloric acid samples are outlined. Also given are the working curves and deviations of both elements."

From Summary: "The trajectories of waterdrops in air flowing over airfoils are determined for three airfoil-angle-of-attack combinations using the differential analyzer to solve the differential equations of motion of the waterdrops. From these trajectories the rate of water impingement, the area of impingement, and the distribution of impingement are determined as functions of two dimensionless moduli. Comparisons are made of the rate of water impingement on these airfoils and the rate of water impingement on cylinders."

From Summary: "The trajectories of waterdrops in air flowing over airfoils are determined for three airfoil-angle-of-attack combinations using the differential analyzer to solve the differential equations of motion of the waterdrops. From these trajectories the rate of water impingement, the area of impingement, and the distribution of impingement are determined as functions of two dimensionless moduli. Comparisons are made of the rate of water impingement on these airfoils and the rate of water impingement on cylinders."

"The trajectories of waterdrops in air flowing over airfoils are determined for three airfoil - angle-of-attack combinations using the differential analyzer to solve the differential equations of motion of the waterdrops. From these trajectories the rate of water impingement, the area of impingement, and the distribution of impingement are determined as functions of two dimensionless moduli. Comparisons are made of the rate of water impingement on these airfoils and the rate of water impingement on cylinders" (p. 1).

Report presenting testing of three rocket-powered models with Douglas D-558-2 wings as horizontal fins with scaled structural parameters to determine whether the possibility of wing flutter due to torsion and bending exists in full-scale airplanes at transonic speeds. No wing flutter was present in the models tested, but pitching oscillation developed as it passed into the transonic range.

Abstract: "Following nitrate removal by means of a three-stage hydrochloric acid digestion, uranium was reduced with chromous sulfate reagent. In an inert atmosphere, the quadrivalent uranium was titrated at 80-95[degrees] with standard ferric sulfate solution. The end point was obtained with a potentiometric cell including a platinum in-titrant reference electrode and a platinum indicator electrode. Application was made to various low leverl uranium solutions. For samples containing 1 - 12 milligrams or uranium, less than one percent error may be expected. Iron and chromium do not interfere."

Memorandum presenting the results of a wind-tunnel investigation of the low-speed aerodynamic characteristics of a horizontal-tail model of aspect ratio 2 with an unswept plan form and of a two-dimensional model. The two-dimensional model provides data which can be used as the basis for computing the three-dimensional lift and hinge-moment parameters by the lifting-surface-theory procedure. Results regarding the effectiveness and hinge-moment parameters, static longitudinal stability, scale effect, effect of standard roughness, and effect of removing the elevator nose seal are provided.

Memorandum presenting limited data covering extension of the transonic-flight tests of the XS-1 airplane. The data show that successful flight to a Mach number of 1.35 has been achieved at altitudes up to 40,000 feet.

Report presenting the effects of changes in Reynolds number on the longitudinal aerodynamic characteristics of a 52 degree sweptback wing with an aspect ratio of 2.88 and NACA 64(sub 1)-112 airfoil sections. The model was tested with the leading edge both smooth and rough. Results regarding force and pitching-moment results, flow observations, and discussion of force and moment characteristics are provided.

Report presenting an investigation of the performance of a single can-type combustor designed for a turbojet engine equipped with an 11-stage axial-flow compressor and a single-stage turbine. The investigation was conducted to determine the altitude operational limits of the engine for two fuels, combustion efficiencies at various simulated conditions of altitude and engine speed, combustor-outlet temperature distribution for several altitudes at constant engine speed, and combustor total-pressure drop.

"The experience at Oak Ridge National Laboratory in decontamination equipment and working areas from radioactivity has been summarized." The methods and reagents that were used for decontamination are discussed.

"Finally the work of the report is applied exclusively to consideration of the turbine-propeller power plant because previous performance analyses of the various gas-turbine propulsion systems combine with recent improvements in propeller design indicate that it is this combination which, will give the best over-all performance in the speed ranges considered" (p. 5).