Report describing the effects of pile irradiation on fuel materials and coil springs for the Submarine Intermediate Reactor. The investigation was called for by Hanford Irradiation Request No. 79. Results of investigation are detailed in the report.

From Summary: "Tests and calibrations of an AWS instrument shelter were made in the Langley 300 MPH 7- by 10-foot tunnel for the Signal Corps, U.S. Army. The behavior of the wind vane, the 3-cup anemometer, and the shelter cover was determined in wind speeds up to 150 miles per hour. It was discovered that the rotational speed of the anenometer was greatly influenced by the location, with respect to the wind direction, of three spacer posts that held two upper bays of instruments above the anenometer."

"A general method has been developed for calibrating strain-gage installations in aircraft structures, which permits the measurement in flight of the shear or lift, the bending moment, and the torque or pitching moment on the principal lifting or control surfaces. Although the stress in structural members may not be a simple function of the three loads of interest, a straightforward procedure is given for numerically combining the outputs of several bridges in such a way that the loads may be obtained. Extensions of the basic procedure by means of electrical combination of the strain-gage bridges are described which permit compromises between strain-gage installation time, availability of recording instruments, and data reduction time" (p. 1).

This document describes a method in determining solid solubilities using strain-aging techniques, explaining a non-uniform yielding of the alloy in question.

Report presenting the results of an investigation to determine the effects of a small jet of air exhausting from the nose of an elliptical body of revolution upon boundary-layer transition and the viscous, pressure, and total drag of the forebody at three body stations at Mach number 1.62. The jet effects on body pressure, pressure variations, boundary-layer transition, and total drag are provided.

Technical report describing and comparing drilling methods.

Introduction: "This report is an extension of NAA-SR-Memo-178. The results show the number of control rods as a function of the amount of reactivity to be controlled. Numerical solutions are given for a typical example and are readily obtainable for other cases."

From introduction: "The tube arrangement covered in this report was proposed in June, 1950, as a means of halving the weight and volume required for the heat exchanger. Ideally, the pressure drop across this arrangement should be little more than that required to overcome the skin friction on the tube surfaces. If the pressure drop across the tube spacers and in the cross-flow regions can be kept low, this ideal can be approached. much of the test work covered in this report was devoted to this phase of the problem."

Report presenting an investigation of the effects of the wake resulting from control-surface deflection on the internal performance of two supersonic diffusers and on the engine-body interference drag in the 8- by 6-foot supersonic wind tunnel at Mach number 2.0. Results regarding the internal-flow evaluation, high-pressure-recovery diffuser, and drag evaluation are provided.

Report presenting lateral and directional dynamic response characteristics of a 35 degree swept-wing fighter-type airplane determined from flight measurements and compared with predictions based on theoretical studies and wind-tunnel testing. Results regarding the frequency responses, theoretical and experimental transfer functions, stability derivatives, aeroelastic effects, response at low frequency, and effects of minor derivatives, product of inertia, and flight-path angle are provided.

Report presenting an investigation to evaluate the effects of an all-movable horizontal tail on the longitudinal characteristics of a sweptback wing and a fuselage of a type suitable for long-range high-speed airplanes. Tests were conducted at low speed and at high Mach numbers over a range of Reynolds numbers. Large reductions in longitudinal stability of the wing-fuselage-tail combination were found at lift coefficients well below the stall.

Report discussing an investigation of the longitudinal stability, trim, and drag of a rocket-propelled model at low lift coefficients at a range of Mach numbers. the configuration included a wing and horizontal tail of aspect ratio 4 and thickness ratio in the streamwise direction of 6 percent.

"An investigation was made of the performance of nine conical cooling-air ejectors at primary jet pressure ratios from 1 to 10, secondary pressure ratios to 4.0, and a temperature ratio of unity. This phase of the investigation was limited to conical ejectors having shroud exit to primary nozzle exit diameter ratios of 1.06 and 1.40, with several spacing ratios for each. The experimental results indicated that the pumping range and amount of cooling-air flow obtained with a 1.06 diameter ratio ejector were relatively small for cooling purposes but that the maximum possible thrust loss, which occurred with no secondary flow, was only 7 percent of convergent nozzle thrust" (p. 1).

Report presenting a preliminary investigation of a wedge-type compression surface mounted vertically in a circular cowling conducted in the supersonic wind tunnel at a Mach number of 1.90 and range of angles of attack. With symmetrical cowling, the pressure recovery and stability characteristics comparable to a conical inlet were obtained, but twin-duct flow interaction was observed. Results regarding the pressure recovery and stability characteristics and effects of removing the lower cowl lip and perforating the wedge centerbody are provided.

Leaching and filtration tests were conducted on dump samples and current residues from Afrikander Lease and Babrosco properties on the Witwatersrand, South Africa.

Report discussing studies regarding the properties and nuclear constants of xenon, an element relevant to use of high power thermal neutron reactors.

Abstract: "Methods for recovering radium from K-65 residue have been investigated. A process using Versene was developed and demonstrated on a laboratory scale. In this process K-65 residue is leached with Versene solution and radium is adsorbed from the leach liquors and purified by the use of cation exchange resin."

Report presenting tests to investigate the use of a simple centering spring, which had no variation of force gradient with impact pressure, as an artificial feel device for the elevator control of a fighter airplane. Testing was conducted using a Chance Vought F4U-4B airplane equipped with power controls. Results regarding the force experienced and effects of the feel system are provided.

In this report it reviews a possible declassification of the content of report CP-2782 (February 15, 1945) that presents the data of the most careful measurements of the thermal neutron cross section of 9.2h Xe135 and re-evaluation of the particular methods of measuring neutron flux employed in this experiment had been made for other purposes.

Report presenting free jet tests of a model of the inlets and forebody of the McDonnell XF3H-1 airplane with the original and two alternate nose shapes. Results regarding the total-pressure recovery after diffusion, maximum mass-flow ratio, inlet total-pressure profile, shadowgraphs, flow variation, and pressure oscillations are provided.

This following report discusses certain topics pertinent to the x-ray photometric method, such as the optimum size of sample and of sample concentration, the technique of measurement for high precision, the use of easily prepared uranium standards for future calibrations and corrections for extraneous substances, and it compares results obtained by both x-ray and chemical assays.