Tests on twenty identically prepared 26 gauge Chromel-Alumel thermocouples have been completed. It appears that wires of this material without protection are unsatisfactory mechanically and thermoelectrically for service in atmospheres of CO₂ at 1000°C.

"A rapid design method based on stream-filament techniques was developed to obtain the boundaries of an annular combustor-inlet diffusr from a given stagnation streamline, given boundaries of the combustor liner, and given inlet and terminal velocities" (p. 1).

Report presenting an investigation of several methods of straightening diffuser-exit total-pressure profiles produced by a typical half-conical double-shock side inlet at a free stream Mach number of 3.05. The methods included the use of longer subsonic diffusers, constant-area mixing sections at the diffuser exit, internal screens, a rapid acceleration of the flow at the diffuser exit, internal bleed, and a change in internal-flow passage shape obtained by raising the internal centerbody fairing from the floor into the diffuser duct. Each of the methods was found to be effective in reducing distortion.

From Summary: "Experimental performance of a rocket engine using 15 percent fluorine-85 percent oxygen and JP-4 was compared with that obtained using oxygen and JP-4. The regeneratively cooled engine was operated at 5000 pounds thrust and a chamber pressure of 350 pounds per square inch absolute. The peak specific impulse from 15 percent fluorine was 251 pound-seconds per pound. This is an increase of 3.3 percent over the 243 pound-seconds per pound obtained with fluorine."

Report presenting an investigation of ram-jet-engine control by shock positioning on a 16-inch fixed-geometry ram jet at a range of free-stream Mach numbers. The control method appears to offer adequate control of ram-jet-engine operation. Results regarding the steady-state performance, effect of control settings on response and stability, effect of disturbance size and Mach number on response to fuel-flow disturbances, Mach number disturbances, angle-of-attack disturbances, exhaust-area disturbances, and recovery from subcritical engine operation are provided.

"A free-jet investigation of the performance of the XRJ43-MA-3 ram-jet engine has been conducted in an altitude test chamber at the NACA Lewis Laboratory. It is the purpose of this report to compare the performance and rich blow-out limits of the various engine configurations and diffuser orientations with the basic or standard engine configuration" (p. 1).

Report presenting the reverse-thrust performance of several tail-pipe-cascade-type model thrust reversers over a range of exhaust-nozzle pressure ratios from 1.2 to 2.4. Both symmetrical and asymmetrical cascade blade shapes were investigated. Results regarding the performance of tail-pipe-cascade-type model thrust reversers having symmetrically shaped cascade blades and the performance of tail-pipe-cascade-type model thrust reversers having asymmetrically shaped cascade blades are provided.

Report discussing testing on a model of the General Electric P-1 nuclear powerplant to determine its internal aerodynamic characteristics. The main purposes of testing were to measure the mass-flow distribution of air, to measure the total-pressure losses for the duct components and complete model, and to determine modifications necessary to attain the desired performance characteristics.

This report describes the results of evaluation tests made on several glass-coated bayonet heaters supplied to Separations Equipment Development by the Pfaudler Company. The glass-coated heaters were found to be resistant to thermal shock, mild mechanical shock, and chemical attack by boiling 60% nitric acid.

A theoretical analysis of the thickness vibrations in long thin rods of barium titanate is presented. The theoretical results are checked experimentally and their meaning discussed.

From Summary: "A free-flight investigation over a Mach number range from 0.6 to 2.0 has been conducted to determine the longitudinal aerodynamic characteristics and effect of rocket jet on zero-lift drag of 1/5-scale models of two ballistic-type missiles, the Hermes A-3A and A-3B. Models of both types of missiles exhibited very nearly linear normal forces and pitching moments over the angle-of-attack range of 8 deg to -4 deg and Mach number range tested."

Attached hereto are copies 1 through 4 of a classified secret report titled "Purex - A Hanford Separations Plant." We are also sending under separate cover a classified confidential report No. HW-36496 titled "Photographs of Purex - A Hanford Separations Plant," which is a counterpart of the above report. These documents are submitted for publication and should be incorporated as a single article.

The purpose of this work was to produce a reliable, inexpensive instrument for the detection of hard beta contamination on the clothing of personnel. Also, the monitoring was required to be accomplished without interrupting the normal activities of the employees.

Report presenting an experimental investigation to determine the effect of rotor leading-edge sweepback on the aerodynamic performance of a transonic turbine. Using an unmodified stator with the modified rotor resulted in large incidence angles at the rotor mean and tip sections.

Report presenting an investigation of a wing swept back 35 degrees in combination with one basic body and three modified bodies at a range of Mach numbers from 0.60 to 1.20. Results regarding force studies and pressure studies are provided. The bodies modified according to the Kuchenmann ring-vortex method resulted in superior aerodynamic characteristics except with regard to zero-lift drag at high supersonic Mach numbers.

Report presenting an investigation at low speeds of the static-stability characteristics of a simplified model of an unusual configuration. The model had three identical triangular airfoils of low aspect ratio. Results of tests of the simplified model of the configuration are presented for a large range of angles of attack and sideslip.

Report discussing an investigation of the supersonic area rule using rocket-propelled zero-lift models of straight wing-body configurations at a range of Mach and Reynolds numbers. The body was modified with symmetrical indentations according to area-rule considerations in order to reduce wave drag. The indentations were found to have an effect at Mach numbers 1.10 and 1.41 but did not have any benefit above Mach number 1.3.

Thus we see that the derivation of elementary age theory is based on replacing the probability of collision governed by the Milne kernel by a Gaussian probability having the same zeroth and second moments. It is apparent that the age theory distribution will fail close to the source and at many free paths from the source.

Report presenting a blade-vibration and rotating-stall survey on a production turbojet engine with a 13-stage axial-flow compressor with a pressure ratio of 7 and an air flow of 120 pounds per second. Results regarding stall patterns, maximum vibratory stresses, and location of the stall zones are provided.

Memorandum presenting an investigation to determine the static longitudinal and lateral stability and control characteristics of an airplane configuration with a trapezoidal wing with modified hexagonal airfoil section and tail surfaces with 5 degrees semiangle wedge sections carried out in the 11-inch hypersonic tunnel.

From introduction: This report covers an investigation of solid-state bonding as a technique for aluminum cladding uranium plates of 3 by 0.180-in. cross section in lengths up to 14 ft.

Report presenting an investigation of the performance of pentaborane fuel at relatively low equivalence ratios using a 9.75-inch-diameter ramjet engine using pentaborane at an average equivalence ratio of approximately 0.23. Time histories of the flight conditions and combustion chamber conditions, total-temperature ratio, fuel flow, pressure recovery, thrust, propulsive thrust, and drag coefficients, and comparison with hydrocarbon fuel are provided.

Abstract: "A possible mechanism for the generation of magneto-hydrodynamic whirl rings near the center of the sun is described. The organic relation of the reflection of these whirl rings at the surface of the sun to the cooling of sunspots, orientation, and polarity sequence of sunspots, prominences, flares, and faculae is delineated."