From introduction: This report is a compilation of the presently available data pertaining to the proposed reactor power plant site which may be used in evaluating the proposed measures for protecting the public from possible radioactive hazards, both during normal operation and under unusual hazards.

From introduction: This is Progress report BMI-282, the first of a series covering the operation of the pressure-leaching towers for the extraction of uranium by an ammonium carbonate leach...This report discusses the data obtained from tests run to show the effects of such variables as the amount of air and carbon dioxide passed through the pulp, temperature, pressure, and concentration of ammonium carbonate and ammonium bicarbonate in the leach solution on the extraction of uranium.

Abstract: "Sound, fabricable ingots of thorium were produced by triple are melting of electrolytic thorium. Consumable electrodes were fabricated by tack welding of cold-pressed and vacuum-sintered bars of the granular thorium electrodeposited from a molten-salt bath. The hydrogen content of the electrodeposited material was reduced from 80 to 4 ppm by vacuum sintering at 1250 C at pressures below 1 x 10-(-3) mm of mercury. Both sodium and chlorine content were reduced during melting; sodium from 250 to 25 ppm and chlorine from 1000 to 30 ppm. Oxygen and HCl acid-insoluble contents increased during sintering and melting. Oxygen content increased from 0.35 to 0.50 w/o and HCl acid-insoluble content from 0.8 to 4.0 w/o. A starlike includion revealed by metallographic examination of the as-cast thorium was identified as ThO2."

This report discusses three experimental methods used to study the kinetics of the reaction between zirconium and UO2.

From abstract: "Plamons (plasma-magnetic entities) are toroidal "packages" of plasma wrapped up in their own magnetic field. Experimental evidence for the existence of plasmons is adduced and theoretical considerations concerning their various types and their stability are discussed."

Report presenting the results of an experimental investigation of the unsteady lift induced on a wing in the downwash field of an oscillating canard control surface. The results indicated that existing theories provide a reliable guide for the estimation of the magnitude of the lift derivatives and centers of pressure at low values of reduced frequency and low angles of attack.

Report presenting an investigation on canopy pressures and canopy-fuselage forces and moments under conditions of combined pitch and sideslip. The canopy configurations tested varied in windshield shape (flat, vee, and round) and were tested at two Mach numbers and Reynolds numbers.

Report presenting measurements of the longitudinal stability, lift, and drag characteristics of an airplane configuration with a 60 degree delta wing and a swept horizontal tail mounted near the wing plane extended at a range of Mach numbers using the rocket-model technique. Comparisons are made to data form a similar model with the tail mounted above the wing plane.

Report presenting zero-lift drag results for two 60 degree delta-wing configurations with air inlets. One had twin conical-shock semi-circular scoops just ahead of the wing-body juncture and one had a modified wing section over the inboard portion to allow installation of modified triangular inlets in the wing leading edge. Results regarding the drag coefficients and mass-flow ratios are provided.

Report presenting an investigation of a configuration with a body of fineness ratio 16.9, a 52.5 degree sweptback wing of aspect ratio 3, taper ratio 0.2, and NACA 65A004 airfoil section, and an incline tail which was aeropulsed continuously in pitching during free flight with and without a sustainer rocket motor operating. The Mach number range covered was from 1.4 to 2.3. Results regarding drag, total normal force and pitching moment, wing normal-force-curve slope, flow conditions at the horizontal tail, and cross coupling are provided.

Report discussing testing of a multijet 60 degree delta-wing airplane configuration with twin-engine exhausts at specified locations under the wing. Data was obtained for jet-on and jet-off conditions between a range of Mach numbers. Results are presented for the effect of jet on drag, jet effect on lift, static longitudinal stability, and dynamic longitudinal stability.

Report presenting an investigation in the 16-foot transonic tunnel to determine the lateral-control effectiveness of differentially deflected horizontal-tail surfaces mounted behind a 45 degree sweptback wing-fuselage combination. The effectiveness of the differentially deflected horizontal tail as a lateral-control device was found to be essentially independent of angle of attack and Mach number even in the transonic region. Results regarding the effects of differential deflection of horizontal-tail surfaces and effects of the vertical tail are provided.

Report presenting an investigation in the transonic pressure tunnel to determine the aerodynamic loading characteristics of a 60 degree delta wing in the presence of a body with and without body indentation in accordance with the transonic-area-rule concept. Tests covered a range of angles of attack and Mach numbers. Results regarding force and moment coefficients and curves are provided.

Memorandum presenting an investigation carried out in the 11-inch hypersonic tunnel to determine the static longitudinal and lateral stability and control characteristics of an airplane configuration with a trapezoidal wing with a modified hexagonal airfoil section and equipped with various tail airfoil sections and tail arrangements. The tests were made at Mach number 6.86 and Reynolds number 343,000 based on the wing mean aerodynamic chord.

Report presenting results from a flight program conducted to obtain information on the airplane response and actual rates and amounts of control motion used by service pilots to perform squadron operational training missions, which are correlated with the airplane handling qualities and calculated maximum dynamic response. Results regarding longitudinal characteristics, rolling characteristics, and sideslip characteristics are provided.

From Summary: "This report treats the Kernel function of the integral equation that relates a known or prescribed downwash distribution to an unknown lift distribution for harmonically oscillating wings in supersonic flow. The treatment is essentially an extension to supersonic flow of the treatment given in NACA report 1234 for subsonic flow. For the supersonic case the Kernel function is derived by use of a suitable form of acoustic doublet potential which employs a cutoff or Heaviside unit function. The Kernel functions are reduced to forms that can be accurately evaluated by considering the functions in two parts: a part in which the singularities are isolated and analytically expressed, and a nonsingular part which can be tabulated."

Report discussing an investigation to determine the free-jet performance characteristics of the XRJ43-MA-3 20B3 ram-jet engine at a Mach number of 2.70 at several angles of attack, inlet temperatures, and fuel-air ratios. Information about the inlet supercritical mass-flow ratio, diffuser-outlet Mach number contours, and effect of angle of attack and inlet temperature on engine performance is provided.

Memorandum presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference performed in the 4- by 4-foot supersonic pressure tunnel at a Mach number of 1.6 in which separate forces on a store and on a 60 degree delta-wing-fuselage combination were measured. The configuration in this report simulates a heavy-bomber delta-wing airplane and has a large external symmetrical store that represents a nacelle with a frontal area equivalent to a twin-engine nacelle.

Memorandum presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference in the 4- by 4-foot supersonic pressure tunnel at a Mach number of 1.61 in which separate forces on a store, a fuselage, a swept wing, and a swept-wing-fuselage combination were measured. The report presents data on a configuration which simulated a fighter-bomber airplane with a large and a small external store.

Memorandum presenting a review of some of the analytical and experimental studies of the use of liquid hydrogen as a jet-engine fuel and which show the possible extension of aircraft performance that will follow adequate research and development effort on the problem of its use.

Memorandum presenting an investigation conducted in the supersonic pressure tunnel on canopy pressures and canopy-fuselage forces and moments under conditions of combined pitch and sideslip. The canopy configurations tested varied in windshield shape, location on the fuselage, and fineness ratio. Results regarding force and moment data, pressure data, and force and pressure correlation are provided.

Report presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.61. Separate forces on a store, a swept wing, and a swept-wing-fuselage combination were measured. This report presents data on a configuration that simulated a fighter-bomber airplane with a large and a small external store.

Report discussing factors influencing flight range and aerodynamic heating for hypersonic boost-glide aircraft. The possibility and advantages of flight at very high altitude to reduce aerodynamic heating and encourage the preservation of laminar flow on the surface of the aircraft is explored.

"In the development of high temperature materials of the brittle category, the need to improve their impact strength for some applications has brought with it a demand for a simple machine for measuring impact resistance, both at room and elevated temperatures, and preferably one in which corrections such as the toss energy are negligible. This report describes such a machine and presents the results of some preliminary tests on the effect of temperature on impact strength of several alloys and cermets. A comparison is also given between the impact resistance of notched and unnotched specimens" (p. 1).