Report presenting tests of the extent of laminar flow that can be obtained with practical wing-surface conditions. Chemical sublimation was used for boundary-layer-flow visualization on the wings of a supersonic fighter airplane in level flight. A method of continuous monitoring using heat temperature resistance gauges was also used on one wing.

Results regarding testing of steel projectiles fired into copper targets at velocities from 5,000 to 11,500 feet per second, which indicated that as target temperature is increased, the crater size also increases. Twenty-two caliber steel cylinders and steel spheres were used as projectiles.

Chemical sublimation has been employed for boundary-layer-flow visualization on the wings of a supersonic fighter airplane in level flight at speeds near a Mach number of 2.0. The tests have shown that laminar flow can be obtained over extensive areas of the wing with practical wing-surface conditions. In addition to the flow visualization tests, a method of continuously monitoring the conditions of the boundary layer has been applied to flight testing, using heated temperature resistance gages installed in a Fiberglas "glove" installation on one wing. Tests were conducted at speeds from a Mach number of 1.2 to a Mach number of 2.0, at altitudes from 35,000 feet to 56,000 feet. Data obtained at all angles of attack, from near 0 deg to near 10 deg, have shown that the maximum transition Reynolds number on the upper surface of the wing varies from about 2.5 x 10(exp 6) at a Mach number of 1.2 to about 4 x 10(exp 6) at a Mach number of 2.0. On the lower surface, the maximum transition Reynolds number varies from about 2 x 10(exp 6) at a Mach number of 1.2 to about 8 x 10(exp 6) at a Mach number of 2.0.

"The performance and operational characteristics of two afterburner configurations for the Iroquois turbojet engine were evaluated in an altitude test chamber over a range of afterburner equivalence ratios at afterburner-inlet pressures from 733 to 3186 pounds per square foot absolute. These conditions correspond to an altitude range from 38,700 to 66,800 feet at a flight Mach number of 1.5. The only difference between the two afterburner configurations was in the pattern of afterburner fuel injection. At an afterburner-inlet pressure of approximately 3100 pounds per square foot absolute, corresponding to an altitude of 38,700 feet and a flight Mach number of 1.5, the combustion efficiency of both configurations reached peak values of 0.80 to 0.85 at equivalence ratios of 0.35 to 0.40" (p. 1).

"Operation of the original engine configuration disclosed a severe compressor stall problem at high altitude, which was largely attributed to a radial flow distortion entering the high-pressure compressor. Engine modifications for eliminating or alleviating the stall problem were investigated. These included use of variable high-pressure compressor inlet guide vanes, increased turbine-stator areas, and minor alterations in both the low- and high-pressure compressor rotors" (Abstract).

Report presenting an examination of creep and thermal buckling in order to determine their effect on the design of structures for high-speed aircraft. Consideration is given to the use of insulation as a means of alleviating the effect of aerodynamic heating. Creep did not appear to be a significant factor, but thermal buckling may have a substantial effect on the structural design.

Report presenting an investigation to show the effects of systematic changes of leading-edge radius, aspect ratio, Reynolds number, and Mach number on the static longitudinal aerodynamic characteristics of sweptback wings in the 19-foot pressure tunnel. Results regarding the effects of leading-edge radius and aspect ratio and effect of Reynolds number and Mach number are provided.

Report presenting an investigation of control systems suitable for target-seeking missiles. Testing occurred in the free-flight tunnel of the GB-5 glide bomb equipped with a light-seeker control unit which applied flicker control. Results indicated that good stability could be obtained with the control system, but was somewhat less stable than with a proportional control system.

Memorandum presenting an experimental investigation of the elastic compressive buckling strength of plates with various configurations of integral stiffening. Some of the configurations tested included ribbing that was longitudinal, transverse, longitudinal, and transverse, and skewed at various angles to the sides of the plates to form a diamond or waffle-like pattern. The results indicate that the waffle-like stiffening is of sufficient structural interest to merit further study of the plastic buckling and fabrications aspects.

Report presenting an experimental investigation to determine the performance characteristics of two side inlets of different shapes. One had a trapezoidal cross section and one was circular and both were fitted with different lips but the same compression ramp. Results regarding pressure recovery, drag, airflow stability, total pressure distribution, and net propulsive force are provided.

Report presenting the results of an investigation to develop a metal-bonding adhesive with improved heat-resistant properties. The most promising results were obtained with a formulation of a phenol resin and epoxy resin with certain heat stabilizers and catalysts. Results regarding the strength of bonds, resistance of adhesives to aging, and heat-resistant properties are provided.

Report presenting characteristic exhaust-velocity measurements made of the JP-4 fuel-red fuming nitric acid propellant combination in 40-pound-thrust rocket engines with various combustion-chamber lengths and diameters. The results are compared to those from previous studies and discussed in terms of a vaporization model of combustion. Results regarding the effect of UDMH, effect of water on performance of hydrocarbon fuels, effect of water on performance of hydrazine fuel, and some of the chemical and physical factors affecting combustion are provided.

Report presenting the performance of three injector types in a 2400-pound-thrust rocket test chamber. Characteristic velocity and specific impulses were obtained over a range of oxidant-to-fuel ratios at a nominal chamber pressure of 600 pounds per square inch absolute. RMI-1 and 2 had fairly similar results, but RMI-3 gave no stabilized data due to combustion instability.

Results regarding testing of steel projectiles fired into copper targets at velocities from 5,000 to 11,500 feet per second, which indicated that as target temperature is increased, the crater size also increases. Twenty-two caliber steel cylinders and steel spheres were used as projectiles.

From a theory developed on a quasi-one-dimensional-flow basis, it is found that the stability of the ram jet is dependent upon the instantaneous values of mass flow and total pressure recovery of the supersonic diffuser and immediate neighboring subsonic diffuser. Conditions for stable and unstable flow are presented. The theory developed in the report is in agreement with the experimental data of NACA-TN-3506 and NACA-RM-L50K30. A simple theory for predicting the approximate amplitude of small pressure pulsation in terms of mass-flow decrement from minimum-stable mass flow is developed and found to agree with experiments.

Report issued by the APDA over a design study conducted on an "in-pile package loop for use as a reactor fuel test facility" (p. 5). The results are presented and discussed. This report includes tables, and illustrations.

From abstract: Two 20-ft-long 7-ft-diameter 10-gauge structural-plate pipes, having longitudinal joints with eight bolts per foot, were buried and tested in the Smoky event of Operation Plumbbob at predicted pressure levels of 195 and 265 psi. The depth of burial was 10 ft over the crown of the pipe.

From abstract: "The present paper proposes a lattice test pile, (or LTP) as an alternate to the continuing program of building up and tearing down of exponential piles."

From introduction: "The discovery of element number 96, curium, was realized by the preparation and identification of the isotope Cm-242 by G. T. Seaborg, R. A. James and A. Ghiorso by cyclotron bombardment of Pu-239 with helium ions."

The following report is focused on finding the measurements of low temperature heat capacities of neptunium dioxide. The entropy and the interpretation of the anomaly in the heat capacity curve will be dicussed."

This report follows experiments on K[infinity], measuring the element for several red sizes, enrichments, and water-to-uranium volume ratios-(1, 2), by making use of the relation k[infinity] = 0M-[2]B-[2] (M-2 = migration area, B = buckling). The purpose of this report is to compare the experimental data for k[infinity] with values calculated from the four-factor formula k[infinity] = [eta][epsilon]pf.

"The purpose of this specification is to describe a procedure for preparation of pure BF3 gas, suitable for use in BF3 proportional neutron counters."

The examination of 3 districts; southeastern Pennsylvania near Chester and Philadelphia, the Williams quarry northeast of Kaston, and the northeastern end of Mt. Pisgah near Mauch Chunk.

The development of the reactor layout is continuing. New features that have been incorporated because of stress, fluid flow, or fabricability considerations include an elliptical fuel expansion tank, a rounded dome to enclose the top of the reactor, a newly designed sodium pump impeller, and other related items. Recently completed heat exchanger tests yielded consistent data from which a series of heat exchangers is being designed. The most promising of these will be chosen for the ART.