From abstract: This proposal for a 6"D column plant is based on laboratory and pilot plant work done at Oak Ridge and at Model City.

This supplement describes a number of modifications to the Liquid Metal Fuel Reactor Experiment (LMFRE), including (1) engineering design changes to achieve economies in the original reference design, and (2) a revised cost estimate that reapportions the various construction, research and development, and operating costs in accordance with procedures established by the Atomic Energy Commission.

Note presenting the equations of the compressible laminar boundary layer for the windward streamline in the plane of symmetry of a yawed cone. Solutions are obtained for both insulated and cooled surfaces. The heat-transfer rate to this most windward streamline increases significantly with angle of attack.

Report presenting an investigation of the pressure and equilibrium-temperature distributions on a sphere at Mach numbers of 2.00 and 4.15. The local aerodynamic heat transfer was measured on a sphere at Mach number 2.00 and on a hemisphere-cylinder at Mach number 4.15. Results regarding pressure distributions, equilibrium and recovery temperatures, heat-transfer coefficients, and effect of roughness on transition are provided.

Report presenting some information on flow characteristics - velocity field, pressure drop, and friction - for steady, fully developed laminar flow through a duct consisting of two parallel walls, for flow throguh tubes with circular cross section, and for boundary-layer flow over infinite wedges. In order to determine the extent to which the boundary conditions imposed o the flow by the various geometries influence the flow characteristics, dimensionless parameters common to both channel and boundary-layer flow were developed.

Note presenting a subcarrier oscillator which, in conjuncting with a telemetering system, gives a satisfactory method for telemetering temperatures by means of thermocouples from pilotless aircraft. The method results in an oscillator having a small size, low microphonics, high input resistance, and satisfactory stability if a switch is used to commutate calibration voltages along with the pickups.

Report presenting an investigation to study the effects of propeller diameter on the ability of a flapped wing, with and without boundary-layer control, to deflect propeller slipstreams downward for vertical take-off. The results indicated that without boundary-layer control, an increase in the ratio of flap chord to propeller diameter increases the turning angle but decreases the ratio of resultant force to thrust.

From Introduction: "The analysis of flight data in the present report is, to a large extent, based on analyses and information contained in references 1 and 2 for wing deflections, reference 3 for horizontal-tail parameters, reference 4 for airplane lift-curve slopes and angles of zero lift, and reference 5 for wing centers of pressure."

Note presenting a reevaluation of existing flight data obtained for a supersonic canard missile configuration of the boost-glide type to determine derivatives not previously evaluated. The derivatives are utilized to determine some typical airframe frequency responses based on the three-degree-of-freedom longitudinal equations of motion. Results regarding derivatives, frequency responses, and three-degree-of-freedom approach to future automatic-control studies are provided.

Report presenting analytical flutter studies made for 2 two-dimensional fuel-loading wing models, as well as comparisons of experimental results for bending-to-torsion frequency ratios near 1.

A reexamination has been made of the use of simple concepts for predicting the shape and location of detached shock waves. The results show that simple concepts and modifications of existing methods can yield good predictions for many nose shapes and for a wide range of Mach numbers.

Report presenting an investigation of the effect of leading-edge thickness on the flow over flat plates with square and cylindrical blunting at Mach number 4 and free-stream Reynolds numbers per inch of 2380 and 6600. For test conditions, the bow shock wave was detached and leading-edge shape had no effect on surface pressures aft of two leading-edge thicknesses. Results regarding surface pressure, flow-field surveys, heat transfer, boundary-layer thickness, surface pressure distribution, local Mach number, local Reynolds number, and heat transfer are provided.

The effects of overheats to temperatures of 1650, 1800, 1900, and 2000 F were evaluated in terms of the changes in creep-rupture characteristics at 1500 F of S-816 alloy under stresses within the range of rupture strengths of the alloy for 100 to 1000 hours. Overheat periods were predominantly of 2-minute duration and were applied cyclically at approximately 5- or 12-hour intervals. The possible damage from overheating was believed to include internal metal structure changes induced by exposure to the higher temperatures and loss of life by creep if stress was present during the overheats.

From Introduction: "The data included in this report for Nimonic 80A alloy, for instance, represent experiments carried out to help clarify a production problem of grain-size control in an alloy which has been extensively used. The general procedure of the investigation was to carry out controlled laboratory experiments on samples of bar stock to find conditions of heating and hot-working which resulted in abnormal grain growth."

Report presenting an investigation of overheating HS-31 alloy to four different temperatures during the course of rupture tests at 1500 degrees Fahrenheit. The intent was to develop basic information on the effect of overheats on creep-rupture properties so as to assist in the evaluation of damage from overheating during gas-turbine operation. Results regarding the rupture properties of test material, overheating in the absence of stress, overheating in the presence of stress, microstructural effects, comparative effects of overheating on S-816 and HS-31 alloy, mechanism of damage from overheating, and interpretation of results in terms of overheating in gas turbines are provided.

Report presenting turbulent and mean-flow characteristics of several noise-suppression multiple-jet nozzles from hot-wire-anemometer measurements for the flow conditions at Mach number 0.3. The measurements show that turbulent mixing, as indicated by reduced intensity and scale of turbulence, occurs closer to the nozzle in interfering than in noninterfering jets. Results regarding mean flow, turbulent flow, and scale or eddy size are provided.

Note presenting an approximate method for the calculation of compressible turbulent boundary layer with heat transfer and arbitrary pressure gradient. The method involves the momentum integral and moment-of-momentum equations as simplified by using Stewartson's transformation.

Note presenting an investigation to study the interaction of bearing and tensile loads on the creep behavior of joints. A simplified model was employed which contained many of the features found in riveted connections. Results regarding creep-rupture tests, plate subjected to tension, plate subjected to bearing loads, plate subjected to tensile and bearing loads, and index of joint behavior are provided.

From Introduction: "The present paper is to investigate analytically the alleviation that can be obtained by a relatively simple system which alters the longitudinal motions induced by the direct effect of the gust loads."

Report presenting an experimental investigation to determine the dynamic stability and control characteristics of a four-engine-transport vertical-take-off airplane model in the transition range from hovering to normal forward flight. Both flight and static-force tests were conducted and flight testing was carried out with a pitch damper installed. Results regarding longitudinal stability and control and lateral stability and control are provided.

An experiment was conducted to obtain the rate and area of cloud droplet impingement on four bodies of revolution was conducted in the icing tunnel with a dye-tracer technique. The study included several forebody shapes of different fineness ratios over a range of angles of attack and rotational speeds. Results regarding velocity distribution, local impingement characteristics, and correlation of impingement characteristics are provided.

Report discussing the boundary-layer transition and heat-transfer measurements for a model of the Titan intercontinental ballistic missile up to a specified Mach and Reynolds number. Boundary-layer transition was observed on the nose of the missile. The drag coefficient for a variety of Mach numbers was also obtained.

Report presenting an investigation in the 20-foot free-spinning tunnel on a scale model to determine the spin and recovery characteristics of the Douglas F4D-1 airplane equipped with external fuel tanks. Results regarding erect spins, inverted spins, and parachute results are provided.

"For the purpose of calculating bomb trajectories, forces and moments have been measured on bombs of three fineness ratios in the presence of a swept-wing fighter-bomber configuration at a Mach number of 1.61. Trajectories thus obtained have been compared with those from dynamic model tests and an analysis has been made to determine the source of errors and to suggest improvements in both techniques."