From introduction: The study of cyclotron-magnet design presented here is directed toward attaining a large ratio of energy in the ion beam with respect to cost. Alternatively, the goal may be regarded as a smaller, more convenient apparatus. These two objectives are not completely incompatible; a design that is more economical than the usual is also smaller. The best design of a cyclotron can be obtained only by considering the problem as a whole. The conditions necessary to maintain an ion beam, the conditions required for the operation of the oscillator, and a host of other problems influence the design of the magnet. It is assumed in this paper that the "other problems" can be satisfactorily solved, if the gap has a suitable geometry and the field a suitable space dependence.

Technical report outlining the effect of strain rate on the tensile properties of thorium. It has been found that the yield strength increases slightly with increasing strain rate, and that tensile strength increases but to a less extent. Studies on the fabrication of thorium by extrusion and drawing have continued, as have studies on the extrusion cladding of thorium and uranium with zirconium. [From Summary}

"The performance and operational characteristics of a Python turbine-propeller engine were investigated at simulated altitude conditions in the NACA Lewis altitude wind tunnel. In the performance phase, data were obtained over a range of engine speeds and exhaust nozzle areas at altitudes from 10,000 to 40,000 feet at a single cowl-inlet ram pressure ratio; independent control of engine speed and fuel flow was used to obtain a range of powers at each engine speed. Engine performance data obtained at a given altitude could not be used to predict performance accurately at other altitudes by use of the standard air pressure and temperature generalizing factors" (p. 1).

A review of the present design information and studies relating to nuclear power plants indicates that the weight of the power plant components, exclusive of crew shield and nacelles, may at a particular design point be represented by an equation of the form, W{subpp} = W{subo} + K{subt}T. By use of this, a power plant parameter psi is defined as the ratio of the part of the power plant plus nacelle weight that varies with thrust to the net thrust of the power plant less nacelle drag. The funamentall part that this parameter plays in determining the gross weight of a nuclaer powered aircraft is shown. This parameter depends on the design point Mach number and altitude, and the weight and drag increments attributable to the nacelle installation.

None

This quarterly progress report details the ongoing research and experiments at the Oak Ridge National Laboratory as part of the Aircraft Nuclear Propulsion Project. The first part of this report discusses reactor theory and design. The second part of this report is not included. The third part of this report discusses materials research. The fourth part of this report includes appendixes

"A method is described for determining the "displacement surface" of known three-dimensional compressible boundary-layer flow in terms of the mass-flow defects associated with the profiles of the two velocity components parallel to the surface. The result is a generalization of the plane flow concept of displacement thickness introduced in order to describe how a thin boundary layer distorts the outer nonviscous flow. Numerical values are found for the known three-dimensional boundary-layer flow about a cone at a small angle of attack to a supersonic stream" (p. 367).

A study investigated the effects of suction through porous leading-edge surfaces on the longitudinal aerodynamic characteristics of a 47.5 degree sweptback wing-fuselage configuration in the full-scale tunnel. The wing section normal to the quarter-chord line was NACA 64(sub 1)A112, the aspect ratio was 3.4, and the taper ratio was 0.51. Results regarding the basic wing characteristics and effect of area suction on the longitudinal characteristics are provided.

Report presenting an investigation of two versions of a type of forward underslung scoop mounted on a pointed fuselage in the supersonic blowdown tunnel. The scoop entrances were in the shape of a 60 degree sector of an annulus, but the sides of one scoop were sweptback, while the others were unswept. Results regarding the shadowgraphs and surface-pressure distributions and total-pressure recovery are provided.

Monthly activities for the following studies are given: (1) pile graphite monitoring; (2) graphite burnout and chemical studies; (3) graphite physical properties studies; (4) controlled temperature exposure; (5) thermal conductivity of gases; (6) damage mechanism study; (7) special exposures; and (8) experimental graphite program.

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, Price Daniel, regarding a legal question submitted for clarification: Authority of the Commissioners' court to expand county funds to pay expenses for members of the county juvenile department to attend a national conference of juvenile agencies.

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, Price Daniel, regarding a legal question submitted for clarification: Legality of making payments after August 31, 1951, under architect and building contracts executed prior to September 1, 1949.

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, Price Daniel, regarding a legal question submitted for clarification: Legality of altering, repairing, extending the existing air conditioning system for the eleventh floor of the Tribune Building.

Report presenting tests of rocket-propelled models at transonic speeds to compare the zero-lift drags of 45 degree sweptback wings with and without solid nacelles at the wing tips. The wing drag coefficient was lowered at high subsonic and supersonic speeds when the aspect ratio was reduced from 6.0 to 3.55. Results regarding the favorability of the wing-tip nacelles and the force-break Mach number of the varying configurations are also provided.

From Introduction: "The results of this complete evaluation of the altitude performance and operational characteristics of the two types of flame-holder and fuel-system configurations are reported herein.The starting limits of both configurations at a flight Mach number of 0.6 are also discussed."

"An investigation was conducted in the Ames 12-foot pressure wind tunnel to determine the effect of an operating propeller on the aerodynamic characteristics of a 1/19-scale model of the Lockheed XFV-1 airplane. Several full-scale power conditions were simulated at Mach numbers from 0.50 to 0.92; the.Reynolds number was constant at 1.7 million. Lift, longitudinal force, pitch, roll, and yaw characteristics, determined with and without power, are presented for the complete model and for various combinations of model components" (p. 1).

Note presenting a description of basic electrical networks that compensate for the thermal time lag of thermocouple and resistance thermometer elements used in combustion research and in the control of jet power plants. The measurement or the detection of rapid temperature changes by use of such elements can thereby be improved.

An investigation to determine the heat-shock resistant properties of two molybdenum disilicide turbine blades under centrifugal loads imposed by turbine rotation is presented. Molybdenum disilicide turbine blades fabricated by hot-pressing techniques withstood heat-shock conditions under blade centrifugal stresses up to 5350 pounds per square inch. Additional development is required before the heat-shock resistant properties of molybdenum disilicide are satisfactory for turbine-blade application.

Report presenting an investigation of the effect of combustion on diffusion in the fuel preparation zone of a ram-jet engine. The information was applied in the design of combustor to operate at lean fuel-air ratios.

Report presenting investigations of the effects of fuel properties on combustion-chamber carbon deposition in singe tubular fuel-atomizing and fuel-prevaporizing combustors. The NACA K factor and the smoking tendency were approximately equally effective in relating carbon-deposition data from the prevaporizing and atomizing combustors. Results regarding the K factor, smoking tendency, effect of prevaporizing combustor operating conditions, sulfur, gum, and olefin, are provided.

"Supplementary blade-design data including rotor- and stator-blade coordinates and mean-line angles at the leading and the trailing edges are presented for a transonic axial-flow compressor inlet stage" (p. 1).

Optical and morphological properties of 28 compounds of uranium, plutonium, americium and some related elements, belonging to 21 isomorphous groups, are described. Additional data are given on 5 compounds of similar type described in the National Nuclear Energy Series, Division IV, Volume w, Chapter 19, “Actinide Elements.”

Report presenting the results of a series of qualitative studies with tufts on three wings with sweepback angles of 30 degrees, 45 degrees, and 60 degrees, which show that under certain conditions, a leading-edge vortex can exist in the unsteady flow associated with a gust. The results indicated that if a wing in steady flight prior to entering a gust is at an angle of attack several degrees less than that at which vortex flow first begins in steady flow, it may penetrate the gust without having the vortex develop, even if its angle of attack is increased by the gust into the vortex-flow regime.

A study has been made of the variation of the distance separating bomb and aircraft with time after release as applied to dive-bombing operations, Separation distances determined from this study are presented in terms of two variables only, dive angle and maximum airplane accelerometer reading; the values of separation distance include the effects of delay in initiation of the pull-out and lag in attainment of the maximum normal acceleration. Contains analysis and calculations of the separation distances between bomb and dive bomber following bomb release; separation distances as determined by the dive angle and the maximum airplane accelerometer reading are presented in a single chart.