"An altitude-test-chamber investigation was conducted to determine the operational characteristics and altitude blow-out limits of a Solar afterburner in a 24C engine. At rated engine speed and maximum permissible turbine-discharge temperature, the altitude limit as determined by combustion blow-out occurred as a band of unstable operation of about 8000 feet altitude in width with maximum altitude limits from 32,000 feet at a Mach number of 0.3 to about 42,000 feet at a Mach number of 1.0. The maximum fuel-air ratio of the afterburner, as limited by maximum permissible turbine-discharge gas temperatures at rated engine speed, varied between 0.0295 and 0.0380 over a range of flight Mach numbers from 0.25 to 1.0 and at altitudes of 20,000 and 30,000 feet" (p. 1).

Contains charts for use in determining preliminary values of the spanwise-load, shear, bending-moment, and accumulated-torque distributions of swept wings. The charts are based on strip theory and include four aerodynamic-load distributions, two section-moment distributions, and two inertia-load distributions. The taper ratios considered cover the range from 1.0 to 0 and the results are applicable to any angle of sweep.

"Simultaneous air-flow photographs and pressure-distribution measurements were made of the NACA 4412 airfoil at high speeds to determine the physical nature of the compressibility burble. The tests were conducted in the NACA 24-inch high-speed wind tunnel. The flow photographs were obtained by the Schlieren method and the pressures were simultaneously measured for 54 stations in the 5-inch-chord airfoil by means of a multiple-tube manometer. Following the general program, a few measurements of total-pressure loss in the wake of the airfoil at high speeds were made to illustrate the magnitude of the losses involved and the extent of the disturbed region; and, finally, in order to relate this work to earlier force-test data, a force test of a 5-inch-chord NACA 4412 airfoil was made" (p. 73).

Report discussing flight tests on a low-drag wing pursuit airplane to determine the effects of Mach and Reynolds numbers on the maximum lift coefficient obtainable in gradual and abrupt stalls. The obtainable maximum lift coefficient was found to be greatly affected by the Mach and Reynolds numbers in gradual stall. In abrupt stalls, the maximum lift coefficient was affected by the Mach number, but not the Reynolds number.

Technical report. Long-time tests have been made on the effect of various types of radiation on the corrosion of 2S aluminum in simulated W water. In no case was any acceleration of corrosion by the radiation observed; the effect of radiation, if any, appeared to be a protective one. Deuteron irradiation did accelerate the corrosion of mild steel at low flow rates in hot water of pH 6 to 7, but no appreciable effect was observed with copper, stainless steel, or tuballoy. The general theory of the effect of radiation on corrosion is discussed, with the conclusion that no acceleration of corrosion by radiation is to be expected in most cases of practical interest.

This memorandum presents the process design for the solvent reast area of the Feed Materials Production Center. The purpose ofthe transmittal is to provide the basis for the detailed mechanical design and layout of this section of the refinery. Drawings, flowsheets, and specifications are included.

From Summary: "An investigation of a 0.034-scale model of the production version of the Chance Vought F7U-3 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The inverted and erect spin and recovery characteristics of the model were determined for the combat loading with the model in the clean condition and the effect of extending slats was investigated. A brief investigation of pilot ejection was also performed."

The object of the work done during the month of June has been to assure that deposition of chemically pure chromium metal by gas plating, both by itself, or as a component of nickel-chronium and/or other alloys.

Report presenting an experimental investigation using a 16-inch impulse-type supersonic-compressor rotor as a separate component, which obtained a maximum total-pressure ratio of 5.42 and an adiabatic efficiency of 0.76 at 101-percent design speed. The rotor could operate over a wide range of back pressures, but it did not obtain the design impulse condition. Results regarding the rotor-component investigation and stage investigation are provided.

Report presenting an investigation to determine the effects of pouring temperature and grain size on the uniformity of lives and initial failure times of groups of AMS 5385 gas turbine blades and to relate the individual lives of the blades to grain size. This is due to the fact that the uniformity of lift of cast alloy gas-turbine blades is generally unsatisfactory. Results regarding the metallurgical examination are provided.

Report presenting results of an investigation of the lateral stability and aileron-effectiveness characteristics of a wing with the leading-edge sweepback decreasing from 45 degrees at the root to 20 degrees at the tip. Results regarding the static lateral stability characteristics and aileron characteristics are provided.

The purpose of this document is to describe the design and construction of a full-scale, electrically-heated model of a 19-rod PRTR fuel element for use in heat transfer experiments.

The definition of the Lebesgue integral is used to develop a numerical integration method in which the integral is evaluated directly from a contour plot of the function. It is useful in working from weather maps, potential surfaces, etc., but was particularly designed to assist in reducing blast diffraction space-time diagrams to simple, meaningful quantities.

This report deals with the formation of oriented layers of an oxide which form during oxidation without any evident relationship to the parent and underlying metal. It is offered without explanation or proposed mechanism.

Memorandum presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference performed in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.6. Separate forces on a store, a fuselage, a swept wing, and a swept-wing-fuselage combination were measured. The configuration investigated simulated a heavy bomber airplane with a large store or nacelle with frontal area equivalent to a twin-engine nacelle.

Photogeologic map of the Orange Cliffs-1 quadrangle, Wayne and San Juan counties, Utah

The hazards associated with several possible mechanical failures were analyzed for the PRTR. The consequences of these failures were evaluated for inclusion in the Final Hazards Summary Report.

Report presenting an analysis and examination of a large volume of data from several recent stores-research programs. For a given wing plan form, store position and configuration of angle of attack have been shown to be the most important parameters in the evaluation of store side force.

The stability of fluorothene (polytrifluorochloroethylene, Kel-F) to gamma radiation has been investigated to estimate the probable life expectancy of fluorothene equipment exposed to Purex process solutions. Samples of fluorothene were exposed to total gamma radiation dosages up to 10 degree R. The results of these tests substantiate the findings reported by Sisman and Bopp in their compilation of data on the affects of radiation on plastics.

Report discussing testing of a model of the Douglas A4D-1 to investigate the static longitudinal characteristics of wing and fuselage modifications and the static lateral characteristics of the basic model.

An all-transistor system has been developed to be used in measuring the reactivity of the reactor in the Sandia Engineering Reactor Facility. In operation, the system triggers a pulsed neutron source (PNS) in the reactor and counts the resulting neutron flux, thus giving a measure of the time constant of the reactor. The counting is done in eleven time-sequenced counting channels. The reactor time constant is a measure of the reactor reactivity.

Report presenting an investigation to determine the effectiveness of studying the dynamic characteristics of a low-speed slowly spinning fin-stabilized rocket with a free-oscillation technique and to study certain types of behavior that have been observed in this type of missile. Results regarding the stability of the original model, the effect of reversing direction of arming propeller, the effect of increasing the size of the reversed-rotation arming propeller, the effect of removing the arming propeller, the effect of adding a spoiler nose ring to a basic model, and the effect of changes in the spin rate are provided.

Report presenting an investigation made in the stability tunnel to determine the effectiveness with which the dynamic characteristics of a low-speed slowly spinning fin-stabilized rocket could be studied by a free-oscillation technique and to study certain peculiarities of behavior. Results regarding the stability of the original model, effect of reversing direction of the arming propeller, effect of increasing size of reversed-rotation of the arming propeller, effect of removing the arming propeller, effect of adding a spoiler nose ring to the basic model, and the effect of changes in spin rate are provided.

An investigation has been made in the Langley stability tunnel to determine the low-speed static stability and control characteristics of a model of the Bell MX-776. The results of the investigation indicated that the basic model configuration was longitudinally stable in the angle-of-attack range from about -16 deg. to 16 deg. but that the stability was a minimum near O deg angle of attack. The data indicated an aerodynamic-center position about 0.64 body diameters behind the center of gravity at low angles of attack. Reduction in the size of the front horizontal fins increased the longitudinal stability. With 20 percent of the span of the normal front horizontal fins cut off the aerodynamic center was about 1.04 body diameters behind the center of gravity, and with front horizontal fins having the same area as the front vertical fins, the aerodynamic center was 2.26 body diameters behind the center of gravity (at low angles of attack).