Technical report detailing kinetic equations that have been developed for a boiling-type reactor and inherent reactor stability studies that have been made on the basis of these equations. Presents features of the proposed reactor, comparisons of circulating types, investigations of bubble-rise velocities, effects of transient conditions of vapor mass in steam chest, and bubble time delay functions yield favorable results. [From Abstract]

Thesis analyzing a lead-glass photon spectrometer and its use in studying the absorption of photons and antinucleons.

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.

Memorandum presenting an investigation of the effects of modifying a twin side-inlet duct system on an interceptor airplane as recorded and analyzed over an altitude range from about 25,000 to 51,000 feet throughout the transonic speed range to a Mach number of about 1.2. The modifications consisted primarily of redesigning the inlet lip, increasing the cross-sectional area of the inlet and diffuser, and adding a region of duct contraction ahead of the engine.

Report presenting comparative tests of the rolling power of plain constant-chord, full-delta, and half-delta ailerons on delta wings with varying degrees of sweepback were tested on rocket-propelled test vehicles. Results regarding the effect of leading-edge sweepback, a comparison of rolling effectiveness, and comparison with theory are provided.

Report presenting the pressure-recovery characteristics of a model with two scoops situated on the aft position of a long forebody and connected through diffusors to a common settling chamber at a range of Mach numbers. The effects of interaction between the flow in the two air-induction systems and of varying the mass flow through the boundary-layer scoops were studied. Results at several different angles of attack are provided.

From Introduction: "The data obtained for each configuration are presented in a manner to show the effects of fuel distribution and flame-holder design on net thrust, specific fuel consumption, exhaust-gas temperature, combustion efficiency, operable range of tail-pipe-burner fuel-air ratios, and maximum altitude limit."

A 24-inch-diameter shock-in-rotor supersonic compressor rotor designed to obtain simple radial equilibrium behind the normal shock obtained a maximum total-pressure ratio of 2.02 at an adiabatic efficiency of 0.74 and a weight flow of 61.5 pounds per second at design speed. Although this design method considerably reduced the radial forces, there was no apparent reduction in the radial forces, there was no apparent reduction in the radial redistribution of mass flow over the radial redistribution obtained in the previous investigation. This investigation indicates that the shock boundary-layer interaction pattern and associated effects have a very large effect on the radial redistribution of mass flow through the shock-in-rotor supersonic-compressor rotor.

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 presenting an analysis of the force distribution on a slender pointed body of revolution at angle of attack utilizing pressure-distribution data and balance measurements. The data were obtained in the supersonic tunnel at a variety of Mach numbers and angles of attack. Results regarding normal forces and axial force are provided.

"An experimental investigation of a 0.8 hub-tip radius ratio, nontwisted-rotor-blade turbine designed for a stagnation-pressure ratio of 2.5 and an equivalent mean blade speed of 643 feet per second was made in a cold-air turbine with (a) nontwisted stator blades, and (b) twisted stator blades designed to maintain zero rotor-inlet incidence angles. Turbine efficiencies of the order of 0.85 at the design point were obtained with a nontwisted-rotor-blade turbine with a hub-tip radius ratio of 0.80. The turbine with the twisted stator blades gave higher efficiencies at the design point (of the order of 1.5 percentage points) than the turbine with the nontwisted stator blades" (p. 1).

"The pressure distribution and drag were determined for a spherical-nosed axially symmetric body with thin projecting rods at Mach numbers of 1.76, 1.93, and 2.10. The upstream projection distance of the rods was varied over a wide range to study changes in the character of the flow separation and to determine the variation of drag and pressure distribution with tip projection. Drag coefficients between 0.18 and 0.30 were obtained for most tip projections at each Mach number" (p. 1).

Report presenting the effects of Mach number between 0.50 and 0.95 and between 1.09 and 1.29 on the characteristics of the downwash and on the location of the wake behind a triangular wing of aspect ratio 4 as determined from semispan model tests.

A method is derived for calculating the damping coefficients in pitch and roll for a series of triangular wings and a restricted series of sweptback wings at supersonic speeds. The elementary "supersonic source" solution of the linearized equation of motion is used to find the potential function of a line of doublets, and the flows are obtained by surface distributions of these doublet lines. The damping derivatives for triangular wings are found to be a function of the ratio of the tangent of the apex angle to the tangent of the Mach angle. As this ratio becomes equal to and greater than 1.0 for triangular wings, the damping derivatives, in pitch and in roll, become constant. The damping derivative in roll becomes equal to one-half the value calculated for an infinite rectangular wing, and the damping derivative in pitch for pitching about the apex becomes equal to 3.375 times that of an infinite rectangular wing.

"Absorption measurements have been made in a large body of water to evaluate the contribution to the radiation intensity produced by the degradation of radiation without absorption. Radiation intensities three times those expected from a simple exponential absorption were found. Scattering from the air of gamma radiation has been measured and has been found to agree satisfactorily with theoretical predictions. The penetration of radiation through curved pipes in shielding has been measured and been found to be a flat topped function. A 2" pipe bent in the arc of a circle of 7' chord and a 10' radius gives a reduction intensity over the intensity in air at the same distance of 2.5X10⁴."

Abstract: "A gravimetric procedure is described for the analysis of indium-plutonium solutions. This procedure consists of a preliminary separation of the plutonium as the peroxide, followed by the quantitative precipitation of indium diethyl dithio carbamate from a slightly acid solution. The precipitate is dried at 105 C and weighed. Recoveries of 99.4 - 100.5% with an average precision of 2.3/100 were obtained on known Pu-In solutions containing 5 - 50 mg of indium per sample."

The following report determines how many neutrons are being absorbed in various converter reactor designs, how many neutrons leak from the reactor and the breakdown between fast and thermal leakage. Another interest this paper examines is to determine how many neutrons are absorbed in thorium in the resonance region, at thermal energy, and in the blanket.

The Metallurgy Research Sub-Section at HAPO has conducted a research and development study of a variety of nuclear fuel materials. A summary of the status of the program currently being conducted on ceramic fuel material and a brief discussion of the future program is outlined below.

In the analysis of problems involving transient flow and heat transfer in steam-water mixtures, it is necessary to derive an approximate integral equation of motion for a non-ideal compressible fluid in a duct having finite discontinuities in flow geometry. This equation is derived in this document.

Quarterly summary report of studies conducted through the Radiation Laboratory, University of California. Some results reported in the report may be of a preliminary or incomplete nature.

From Introduction Statement of Objectives: "The purpose of this publication is to provide assistance to the practicing engineer who is faced with the problem of making dynamic measurements of rapidly changing pressures."

Antiproton-production and nucleon-interaction cross sections were investigated for antiprotons in the energy range 0.5 to 1.0 Bev. The antiprotons were distinguished from other particles produced at the Bevatron by a system of scintillation- and velocity-selecting Cerenkov counters. The excitation function and momentum distribution were recorded for antiproton production in carbon and compared with statistical model expectations.

Report containing ongoing projects and experiments undertaken by the Oak Ridge National Laboratory's Molten-Salt Reactor Program.