Report that examines the dose rate of radiation in the air and in a test subject due to radioactive materials (uranium, thorium, and potassium) that are present in the ground. The test subject in these experiments is a water cylinder that is meant to receive radiation in a manner similar to a person.

Memorandum presenting two right circular cylinders tested in axial free flight over a Mach number range of 0.4 to 1.7 by using the rocket-boosted-model technique. Results regarding time history, basic data cross plots, center of pressure, and drag are provided.

Report presenting a brief evaluation of pentaborane-JP-4 fuel mixtures in a turbojet engine at a simulated flight altitude of 50,000 feet and a Mach number of 0.8. Engine data included thrust and specific fuel consumption is provided in tabular and graphical form for various fuel blends as well as photographs of the condition of the engine at the end of the investigation.

From Introduction: "The data presented herein include the standard engine performance parameters of net thrust, specific fuel consumption, and engine total-pressure ratio that reflect the performance available from the use of pentaborane as a fuel. The influence of the boric oxide deposits from the high-concentration pentaborane fuels on engine component performance is presented."

Data were estimated by means of a heat correction equation using data for JP-4 fuel with mixtures of oxygen and flourine. The estimated data were checked for several cases by direct calculations. The difference in specific impulse between the estimated and directly calculated values was from 0.2 to 0.8 pound-second per pound. The maximum value of specific impulse was 334.9 pound-seconds per pound for a combustion-chamber pressure of 600 pounds per square inch absolute and an exit pressure of 1 atmosphere.

Report presenting an analysis to evaluate the effectiveness of supplying secondary airflow for an ejector exhaust nozzle by bypassing from the main inlet. If optimum weight flow is maintained, the performance of the system is about the same as for ejectors supplied by fixed auxiliary inlets up to Mach number 3.0.

Report presenting testing of the subsonic and transonic handling qualities of the Douglas D-558-II research airplane using several configurations of mid-semispan external stores in the altitude region of 20,000 to 40,000 feet. The configurations had an underslung pylon on each wing, pylons plus simulated 1000-pound bombs, and pylons with 150-gallon fuel tanks. Results regarding longitudinal stability and control characteristics, low-speed characteristics, and lateral stability and control characteristics are provided.

Report presenting testing of two identically constructed 2024-T3 aluminum-alloy multiweb-wing structures, models MW-2-(2) and MW-2-(3), under aerodynamic conditions similar to those encountered in supersonic flight at Mach number 2. Results regarding model temperatures, Stanton number, model pressures, model strains, behavior of Model MW-2-(2), and behavior of Model MW-2-(3) are provided.

"A 49 degree swept-wing complete model equipped for high-pressure blowing full span at two chordwise locations at the leading edge of a full-span wing and over a half-span flap has been tested in the Langley full-scale tunnel to determine the effectiveness of blowing at the leading edge as a supplementary leading-edge stall control at high lift coefficients." The effect of blowing on the lift characteristics, pitching-moment characteristics, and drag characteristics of this particular model is described.

Memorandum describing the blades of the tapered-tip 0.4 hub-tip diameter ratio transonic rotor, which were reset 7.5 degrees in the rotor disk and twisted from 0 degrees at the mean-radius section to 4.5 degrees at the tip to increase the specific weight flow approximately 10 percent to 36.3 pounds per second per square foot of frontal area. Results regarding the rotor overall performance, rotor flow parameters, comparison of blade-element performance and design rules, and minimum-loss and choking incidence-angle analysis at rotor hub section are provided.

"Slender-body aerodynamic theory is used in conjunction with thin-plate theory in the flutter analysis of low-aspect-ratio rectangular wings of constant thickness when chordwise variations of deflections are considered. The spanwise variation of deflection is given by a parabola, and the chordwise variation is allowed complete freedom. The results show the variation of flutter speed and mode shape with aspect ratio" (p. 1).

Report presenting an investigation in the transonic tunnel to determine the aerodynamic loading characteristics of a 3-percent-thick, aspect-ratio-2.06, 60 degree delta-wing-body combination at a range of Mach numbers and angles of attack. Results regarding pressure distributions, spanwise loadings, integrated wing coefficients, and tabulated pressure coefficients are provided.

Report presenting an investigation at high subsonic speeds of a complete model with a highly tapered wing and several tail configurations. The complete model was tested with a wing-chord-plane tail, a T tail, and a biplane tail. A discussion regarding the lateral derivatives and sideslip characteristics is provided.

Report presenting an investigation of 6-percent-thick NACA 65-series compressor blade sections in a two-dimensional porous-wall cascade tunnel at several lift coefficients, angles of attack, and solidities. The useful operating angle-of-attack range was generally found to decrease as inlet angle increases.

Memorandum presenting an experimental investigation of four rectangular-throat two-dimensional wedge exhaust nozzles. Three of the nozzles were designed to conform to Prandtl-Meyer streamlines for pressure ratios of 5, 10, and 24, and a fourth, arbitrarily contoured, with a length less than that required for isentropic expansion, was designed for a pressure ratio of about 9.

Report presenting a brief compressor-surge and pressure-recovery program for the Convair YF-102 with a two-spool turbojet engine. The study covered a range of altitudes and Mach numbers.

Report presenting testing of four multiweb wing structures similar to those on an airplane or missile at Mach number 2, sea-level static pressure, a 0 degree angle of attack, and stagnation temperature of 500 degrees Fahrenheit. Three models were made of 2024-T3 aluminum alloy and one was made from SAE 1010 steel; internal structure and skin thickness varied across the models. Results regarding model behavior, model temperatures, calculated skin temperatures, strain-gage results, model pressures, and calculated pressures are provided.

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Will Wilson, regarding a legal question submitted for clarification: Construction of Appropriation contained in Section 7 of Senate Bill 222 of the 55th Legislature - the insurance reorganization bill.

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Will Wilson, regarding a legal question submitted for clarification: Is the Texas State Board of Public Accountancy authorized to hold hearings for the purpose of initiating a complete investigation as an appropriate step of proceedings instituted for the purpose of cancelling or suspending any certificate or permit granted by the Board?

The Nevada Test Site (NTS) Use Committee met Tuesday morning, May 28, 1957, at Mercury, Nevada. This document provides a summary of the meeting.

Abstract: This report presents the results of plant optimization studies and cost estimates of the reference design for a natural uranium, graphite moderated, gas-cooled reactor and power plant which was described in NAA-SR-1833.

Transformation kinetics of binary U -Nb and ternary U-Nb-base alloys were investigated. Additions included zirconium, chromium, titanium, silicon, nickel, nnthenium, and vanadium. Encapsulated samples were given a homogenizstion anneal at 1000 or 1100/sup o/C, water-quenched from 906/sup o/C to retain the phase, and reheated to temperatures between 360 and 600/sup o/C. The metastability of the phase was examined by metallographic, hardness, resistometric, dilatometric and x-ray-diffraction techniques. The U -Nb system is characterized by a monotectoid decomposition of the high temperature allotrope at about 645/sup o/C to form alpha and /sub 2/, a niobium-rich cubic structure. Decomposition in U-Nb and in most U-Nb-X alloys occurred by a continuous precipithtion of alpha from the body-centered cubic phase with a resultant enrichment in niobium of until the equilibrium /sub 2/ composition was reached. In the U-Nb-Ti and U-Nb-V systems, alpha and /sub 2/ were coprecipitated. Annealing at 550 and 600/sup o/C produced decomposition products which, in most materials, originated at the grain boundaries; a fine precipitate which initiated throughout the matrix was observed at lower annealing temperatures. Increasing the niobium content resulted in greatly increased stability. The following elements added to a U-Nb base were found to retard transformation of the phase: zirconium, …

A system for concentrating uranyl nitrate solutions was designed and installed in the Thorex Pilot Plant. A total of 16,060 g of uranium was concentrated in the system in 68 batch runs. A total of 14,400 g total uranium (14.180 g U/sup 233/) was recovered as product suitable for shipment. Uranium loss to the evaporator condensate was 0.03% of ihe total uranium processed. The material balance across the system was 98.4%. The average concentration of uranium in the evaporator feed solution was 29 g/liter; the average concentration in the evaporated solution was 298 g U/liter and in the product solution was 199 g/liter. Radiation readings of bottles containing product solutions were taken with a hard-shell cutie pie immediately after each run, and these readings ranged from 35 to 1100 mr/hr. The radiation levels of the bottles of product solution shipped averaged 78 mr/hr. Bottles of product solution reading in excess of 300 mr/hr, maximum allowable for shipment. were reprocessed in the second-cycle solvent extraction system (Thorex) and reconcentrated. The products from seven runs had radiation levels in excess of 300 mr/hr at the time of concentration, or the activities had grown to that level by the time of shipment. The …

Fission yields were determined from 14-Mev neutrons on U/sup 235/ and U/ sup 238/, thermal neutrons on U/sup 235/, and fission spectrum neutrons on U/sup 235/, U/sup 238/, and Pu/sup 239/. The number of fissions was determined for the Mo/sup 99/ activity. The Sr/sup 90/ was chemically separated and Y/sup 90/ allowed to reach equilibrium. The Y/sup 90/ was separated and counted. (W.D.M.)