Report presenting an investigation at Mach number 4.06 on a typical supersonic airplane model with a 40 degree sweptback wing. The purpose of the investigation was to determine the effectiveness of using wedges on the body and on the vertical tail to increase the static directional stability. Results regarding the longitudinal characteristics and lateral characteristics are provided.

"The lift, drag, and pitching-moment characteristics of a triangular wing, having an aspect ratio of 2 and a symmetrical double-wedge profile of 5-percent-chord maximum thickness at midchord, have been evaluated from wind-tunnel tests at Mach numbers from 0.50 to 0.975 and from 1.09 to 1.49 and at Reynolds numbers ranging from 0.67 to 0.85 million. The lift, drag, and pitching-moment coefficients of the triangular wing with a leading-edge sweepback of approximately 63 degrees did not exhibit the irregular variations with Mach number at high subsonic and low supersonic Mach numbers that are characteristic of unswept wings. The lift-curve slope increased steadily with Mach number below unity and declined slowly beyond the Mach number of 1.13" (p. 1).

Report discussing an investigation of the aerodynamic characteristics of a model of an escape capsule with and without stabilizing fins for a supersonic bomber-type airplane. Lift, drag, longitudinal and lateral stability characteristics, and photographs of the capsule model are presented.

The purpose of the test was to determine if the 1A Canal Water System Demineralizers can be satisfactorily charged with resin. The 1A Canal Water System Demineralizer was satisfactorily charged with resin and conductivity of the demineralizer effluent was less than 0.1 microbes as specified in the Test Procedure.

Report presenting an investigation in the supersonic blowdown tunnel to determine the control characteristics of full-span trailing-edge spoilers on two related full-blunt wings with the same aspect ratio but differing angles of sweepback. A similar unswept wing that was larger and had a partially blunt trailing edge was also tested with a full-span trailing-edge spoiler. Results regarding the lift, rolling-moment, and pitching-moment coefficients for unswept wings, the 45-degree sweptback wing, and a comparison of spoiler data with flap data are provided.

The following report describes a study that was made to adapt a redox method that oxidizes uranium(IV) to uranium(VI) by ferric ion into a microcoulometric method.

The behavior of light and heavy water solutions of boric acid toward pile radiations has been investigated as a function of boric acid concertation. A study has also been made of the effect of hydrogen, hydrogen peroxide, and potassium iodide on the radiation stability of boric acid solutions.

The purpose of the test was to obtain data on the decontamination factors for Cesium-136, Cesium-137, Strontium-92, one hour gross iodine and Iodine-131. This data will be used to determinate efficiency of lithium hydroxide resin for removing radioactive cations and anions. The denomination factors for a particular demineralizer using lithium hydroxide resign were found to vary for different radioisotopes. This variation was from 2.3 for Cesium136 to 77,000 for gross iodine.

The following report describes methods developed for determination of uranium in the alloy.

From introduction: "The purpose of this report is to present some design and construction data for automatic titrators."

"A dynamically similar model of the Army P-38 airplane was tested to determine the best way to land this airplane on the water and to determine its probable ditching performance. The tests consisted of ditching the model at various landing attitudes, flap settings, speeds, weights, and conditions of simulated damage. The model was ditched in calm water from the tank towing carriage and a few ditching were made in both calm and rough water at the outdoor catapult" (p. 1).

Technical report. Photomicrographs showing the effect of heating polished uranium surface at 600, 700, 850, and 1000 degrees C, and sandblasted and cut surface at 1000 degrees C are included.

Report presenting tests to determine the effects of sting-support interference on the zero-lift drag of two bodies of revolution (with and without boattailing). The sting support consisted of a constant-diameter sting followed by a sting flare terminating in a cylindrical support. Results regarding the effect of sting length and sting diameter are provided.

Elevated-temperature properties of titanium carbide base ceramals containing nickel or iron were determined in oxidation, modulus of rupture, tensile strength, and thermal-shock resistance. These materials followed the general growth law and exhibited two stages in oxidation. The following tensile strengths were found at 2000 degrees F: 13.3 weight percent nickel, 16, 150 pounds per square inch; 11.8 weight percent iron, 12,500 pounds per square inch; unalloyed titanium carbide, 16,450 pounds per square inch. Nickel or iron additions to titanium carbide improved the thermal-shock resistance, nickel more. The path of fracture in tensile and thermal-shock specimens was found to progress approximately 50 percent intergranularly and 50 percent transgranularly.

Purpose: "The purpose of the following experiments was to obtain data on the selective extraction of uranium over vanadiur from samples of vanadium ores by leaching with sodium carbonate or sodium bicarbonate solutions, with the object of establishing the time, temperature, and concentration conditions necessary for satisfactory extractions."

"At the request of the Air Materiel Command, Army Air Forces, flight tests were conducted on a P-5lD-20-NA (AAF No. 44-63826) airplane equipped with a horn-balanced rudder. This rudder was fitted with an unbalancing tab as was the original product fan rudder. Tests were made both with the unbalancing tab in operation and with the unbalancing tab locked. The modification to the original vertical tail consisted of removing the cap from the top of the fin and adding 1.91 square feet of area to the rudder as the horn balance and 0.82 square foot of area to the top of the rudder aft of the hinge line" (p. 2).

Report presenting a free-flight investigation of two rocket-powered control research models to determine the force and hinge-moment characteristics at zero angle of attack of a half-delta tip control on a delta wing. Results regarding the control hinge moments, control normal force, and calculated hinge moments are provided.

Memorandum presenting an extension of the tube method of measuring flame velocities to fundamental flame velocities of 141 centimeters per second. The extension was accomplished by reducing the flame-tube diameter from 25 to 12.5 millimeters. Results regarding the gas flow and spatial flame velocity, flame surface area, and fundamental flame velocity are provided.

"The present investigation was conducted in the Langley high-speed 7-by 10-foot tunnel to determine the static longitudinal and lateral stability characteristics at high subsonic speeds of two canard airplane configurations previously tested at supersonic speeds. The Mach number range of this investigation extended from 0.60 to 0.94 and a maximum angle-of-attack range of -2deg to 24deg was obtained at the lowest test Mach number. Two wing plan forms of equal area were studied in the present tests; one was a 60deg delta wing and the other was a trapezoid wing having an aspect ratio of 3, taper ratio of 0.143, and an unswept 80-percent-chord line" (p. 1).

A wind-tunnel investigation of horn balances on a 45 degree sweptback, semispan, horizontal tail surface was made to determine the effects of horn size and inboard-edge fairing at a Mach number of 0.30 and to determine the effects of compressibility up to a Mach number of 0.89. Presented are lift, drag, pitching-moment, and hinge-moment data and lift and hinge-moment parameters.

"The longitudinal stability characteristics of elastic swept wings of high aspect ratio experiencing bending and torsional deformations are calculated for supersonic speed by the application of linearized lifting-surface theory. A parabolic wing deflection curve is assumed and the analysis is simplified by a number of structural approximations. The method is thereby limited in application to wings of high aspect ratio for which the root effects are small" (p. 1).

Technical report outlining measurements of the equilibrium in the exchange of deuterium between ammonia and hydrogen and of the kinetics of this reaction. Details a series of tests carried out to measure Murphree plate efficiencies.

Thirty gram patches of plutonium dioxide can be readily chlorinated by reaction with phosgene or carbon tetrachloride at temperatures of 350 and 450 C respectively. Plutonium trichloride prepared by either method can be reduced to the metal in a hermetically sealed bomb by reaction with calcium. On a twenty gram scale yields of approximately 97 per cent are obtained when a calcium-iodine booster is employed. It has been demonstrated that a method for reduction of plutonium trichloride to the metal without the use of a booster can be development.

"An investigation to determine the steady-state and surge characteristics of the J57-P-1 two-spool turbojet engine with various inlet air-flow distortions was conducted in the altitude wind tunnel at the NACA Lewis laboratory. Along with a uniform inlet total-pressure distribution, one circumferential and three radial pressure distortions were investigated. Data were obtained over a complete range of compressor speeds both with and without intercompressor air bleed at a flight Mach number of 0.8 and at altitudes of 35,000 and 50,000 feet" (p. 1).