"A convenient summary is given of useful formulas on the kinematics of high energy electron scattering together with a derivation of the relevant formulas for transforming from the center of mass to the laboratory system such parameters as scattering cross sections. The formulas derived hold for any two- body collision: the approximation (m = 0) employed for the electron scattering calculations is rigorously true for the elastic scattering of photons."

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In a previous study it was determined experimentally that heat deterioration, or burnout, of the shield masonite is more severe than radiation damage under existing and proposed operating conditions. Higher shield temperatures, which are expected to result from increased power levels, fringe enrichment, and higher graphite temperatures, will markedly increase the rate at which the masonite burns out. The laminated iron-masonite biological shield will lose, as a result of burnout, the hydrogen and oxygen necessary to attenuate and moderate neutrons. The purpose of this production test has been to obtain experimental data from which future shield leakage rates could be estimated. The attenuation data reported here were obtained in the DR pile bulk shield facility from experiments using various void spacings to simulate burnout conditions. From these data it was hoped to determine (1) the resultant attenuation properties of the shields, and (2) the exposure rates due to radiation penetrating the shield.

Report presenting a compressor-rotor-blade vibration survey on a production turbojet engine incorporating a 13-stage axial-flow compressor with a pressure ratio of approximately 7 and an air flow of 120 pounds per second. The investigation was conducted due to the major problem that fatigue failures of compressor rotor blades have caused in the development of the axial-flow compressor. Results regarding rotating stall characteristics, rotor-blade vibration, and fourth-stage rotor-blade failure are provided.

Memorandum presenting a pressure-distribution investigation of a wing of a complete supersonic aircraft configuration as conducted in the 4- by 4-foot supersonic tunnel at Mach number 1.59 based on the mean aerodynamic chord. The experimental life and drag coefficients were less than those predicted by linear theory. Results regarding section pressure characteristics, section characteristics, spanwise characteristics, and overall wing characteristics are provided.

An investigation of the effects of jet nozzle geometry, size of base annulus, and base bleed upon the base and afterbody pressures of a cylindrical afterbody at transonic speeds has been conducted. Sonic and supersonic conical nozzles with jet-to-base diameter ratios from 0.25 to 0.85 were investigated with a cold jet at jet total-pressure ratios up to approximately 8.0 through a Mach number range from 0.6 to 1.25. Base pressure coefficients of about -0.55 were measured for the sonic nozzles at a Mach number of 1 or greater. The jet-to-base diameter ratio had a substantial effect on the base pressure obtained on the cylindrical afterbody of this investigation. Base bleed was beneficial in increasing the base pressure under certain conditions but had little or no effect at certain other conditions.

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Report presenting a cycle analysis of a turboprop engine for various modes of operation over a range of flight conditions in order to determine whether one mode of operation has any marked advantages. The methods of operation explored included constant compressor equivalent design speed, constant design engine rotative speed, adjustable turbine stators, and variable exhaust-nozzle area.

Report of an investigation of the effect of mode of engine operation, engine configuration, and airplane flight condition on the performance and design requirements of a turboprop engine with a high-pressure-ratio single-spool compressor. Both single-spool engines and gas-generating engines are considered. The free-turbine engine was found to be less versatile than the single-spool engine because the range of turbine-inlet temperature over which it can operate is restricted.

The production of U/sup 232/ in the cost optimized TBR and oneregion thorlum oxide-uranium oxide slurry reactor has been estimated to be, respectively, 40 and 260 parts per million parts of U/sup 233/ produced. These production rates are compared with corresponding production rates in irradiated thorium rods and found to be comparable. Recommendations are made for increasing the purity of the U/sup 233/ product. (auth)

"Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 to determine the static longitudinal stability and control characteristics of various arrangements of the Grumman F11F-1 airplane. Tests were made of the complete model and various combinations of its component parts and, in addition, the effects of various body modifications, a revised vertical tail, and wing fences on the longitudinal characteristics were determined" (p. 1).

The results of an experimental investigation of heat transfer to a high velocity, vortex air flow are presented. Heat-transfer coefficients have been observed for vortex flow in tubes which are larger thaa those for linear turbulent flow at a given flow power dlssipation per unit surface area. Comparisons are drawn between air in free- and forced-vortec flow within tubes having length-to-diameter ratios of 11.7 and 20.0, respectively. and linear turbulent flow in identical tubes. For the observed range of flow power disslpation, the freevortex flow system is characterized by a heat-transfer coefficieut one to two hundred per cent larger than that calculated for linear turbuleut flow at the same pumping power. The forced-vortex flow system exhibits a superiority over linear flow only at high flow powers. (auth)

"Preliminary results of one phase of a control-motion study program are presented in the form of plots of load factor.and angular acceleration against indicated airspeed and of time histories of several measured quantities. The results were obtained from 197 maneuvers performed by an F-86A jet-fighter airplane during normal squadron operational training. Most of the tactical maneuvers of which the F-86A is capable were performed at pressure altitudes ranging from 0 to 32,000 feet and at indicated airspeeds ranging from 95 to 650 miles per hour" (p. 1).

Report presenting a low-speed investigation in the stability tunnel to determine the effects of tail height, length, and aspect ratio on the static longitudinal stability and control characteristics of a 60 degree triangular-wing model with twin triangular all-movable tails located near the wing tips.

The drag of a body alone, six triangular wings of various aspect ratios, and the combinations were measured at Mach numbers of 1.50 and 2.02 at a Reynolds number of 5.5 million (based on the body length). The experimental drag-interference results were in accordance with calculations based on NACA RM A9E19, 1949, with skin-friction effects taken into account, the interference effect being principally the result of fixing transition on the body by adding a wing.

Memorandum presenting an aircraft modification involving the incorporation of small canard surfaces into the design, which is meant to compensate for eliminating ailerons. Results of testing in the 20-foot free-spinning tunnel of dynamic models of two sweptback-wing fighter airplanes showed that canard surfaces were very effective in aiding termination of spins of these models. A discussion of the spin tests, catapult and force tests, and effect of jet-engine angular momentum is provided.

A generalization of the Fermi-Thomas model for application of mixtures. This study attempts to determine the equation of state of water up to pressure of 10,000 megabars and temperatures of several thousand electron-volts.

The thenoyltrifluoroacetone (TTA) extraction method has been investigated for the determination of microgram concentrations of thorium in uranium ores and concertrates. The tolerance limits for eighteen elements commonly found in uranium ore concentrates were established. The effect of phosphate on estraction of thorium was studied. Cobalt, copper, tin, and bismuth were found to seriously interfere with the Thoron method for the determination of thorium after a TTA extraction. A TTA extraction method is described for the separation of thorium and uranium from the interfering ions, employing preliminary acid sulfide and ammonium hydroxide separations. The method is rapid, and results obtained compare favorably with results obtained with other procedures. (auth)

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Report presenting the results of short-time creep-buckling and creep-bending tests of 2024-T4 aluminum-alloy columns of slenderness ratio 111 are presented. Tests were performed at 600 degrees Fahrenheit and strain measurements were taken with high-temperature electric-resistance strain gages.

Report presenting testing of rocket-powered models flown at transonic speeds to determine the effect of nacelle location on zero-lift drag. Low drag was obtained between M = 0.80 and M = 0.91 for all the nacelle positions investigated. Nacelles located at the wing tips gave the lowest drag, which was less than the drag of the combination without the nacelles over most of the speed range.

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