BS>Two-group, two-region criticality calculations were made for 10 and 11 ft diameter tanks. The 10 ft tank required a core radius of 102 cm and the 11 ft tank a core radius of 95 cm for criticality. In the calculations, the fluxes were assumed to go to zero at the edge oi the graphite reflector. The fast group of the two-group calculation was broken down into 3 fast groups. The leakage out of the core and reflector for the 4 energy groups is given. (M.C.G.)

From to the files: The Shinarump-Moenkopi contact on Oljetoh Mesa in the Monument Valley district, Arizona-Utah, was examined from November 5 to 15, 1951, to determine the location of and the mineralization in Shinarump channels. Twenty-seven distinct channel outcrops were located and examined. Three of these channel outcrops are mineralized and the remaining 24 are barren. Plate I shows the distribution of the Shinarump, the Moenkopi, and the DeChelly member of the Cutler formation; the location of the Shinarmp channel outcrops; the channel trend where there is good evidence for such a trend. The Hoskinrnini tongue of the Cutler was mapped with the Moenkopi as it is not a good mappable unit in this area. The three mineralized outcrops are indicated by the letters A, G, and AA while the barren outcrops bear the letters B to F and H to Z.

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Report documenting the suitability of Ohio for plant locations to produce synthetic liquid fuels, based on raw materials, water sources, and local interest

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The changes in fuel and poison distributions and the changes in flux shape which accompany the consumption of fuel are studied. The technique employed is a perturbation calculation based on a one-velocity group treatment of the neutrons. The geometry is a spherical core surrounded by an infinite reflector. The programming forms for the IBM-650 which performs the computations using the Wolontis interpretative system are included. Two sample calculations were worked out using the code described and the results are plotted. (M.H.R.)

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Memorandum presenting the design of a piloted combustor intended for a ramjet engine of long flight range. The unit comprises a large annular basket of V-type cross section, the inner surface of which is slotted and bent into small V-gutters.

Report discussing the characteristics of the fuel control of the 48-inch diameter WRJ47-W-5 ramjet engine, including the time history of the fuel system pressures, fuel flow, and engine inlet total pressure. Oscillograph traces for the different variables are provided as well as the accuracy of the calibration factors.

Report discussing heat-transfer and pressure measurements obtained from flight testing of a model of the Titan intercontinental ballistic missile up to a specified Mach and Reynolds number. The heat-transfer coefficients were compared to theoretical results and a discrepancy was found during the accelerating portions of flight. Drag coefficients were obtained for a range of Mach numbers.

Memorandum presenting an investigation of the stability of several bodies of revolution having fineness ratios smaller than 1.0 and having rounded fronts and blunt bases. Free-drop tests were made in the vertical 20-foot free-spinning tunnel to determine the behavior of the various bodies in descent.

Report presenting experimental force and moment data obtained by pressure measurements on a wing of aspect ratio 8.02, 45 degree sweepback of the quarter-chord line, taper ratio of 0.45, and NACA 63(sub 1)A012 airfoil sections, which are compared with the calculated loadings obtained by standard methods and several variations of the methods. Results regarding the system of identifying solutions, spanwise load distribution, lift-curve slope, center of pressure, wing pitching moment, and induced drag are provided.

Report presenting an investigation in the transonic tunnel to determine the flow phenomena, pressure recovery, and external drag of a forward-located underslung air scoop mounted on a basic body of revolution with fineness ratio 11, which when cut off to provide an exit for the internal flow had a fineness ratio of 8. Results regarding the surface pressure distributions, drag, lift and pitching moment, and flow into the inlet on the modified model are provided.

Report presenting an investigation to determine the effect of varying the span and deflection angle of a 15-percent-chord slat on the longitudinal aerodynamic characteristics of a semispan wing with 49.1 degrees of sweepback at the leading edge, an aspect ratio of 3.78, a taper ratio of 0.586, and NACA 65A006 airfoil sections. Force measurements and chordwise pressure distributions were obtained on the wing and extended slat with and without a deflected trailing-edge flap.

Memorandum presenting an investigation of a horn-balanced, flap-type control mounted on a 55 degree sweptback, triangular wing of aspect ratio 3.5 conducted in the 9- by 12-inch supersonic blowdown tunnel. The control exhibited nonlinear variations of hinge moment with both angle of attack and deflection at all Mach numbers. Results regarding control characteristics of basic configuration, effects of control trailing-edge bluntness on control characteristics, and wing characteristics are provided.

The report describes the design of a piloted combustor intended for a ram-jet engine of long flight range. The unit comprises a large annular basket of V-type cross-section, the inner surface of which is slotted and bent into small V-gutters. At the trailing edge of the basket, eight V-gutters are used to propagate the flame into the main stream. A rectangular analog of this combustor was tested at air-flow conditions corresponding to those that might be obtained during cruise.

Report presenting longitudinal trim and drag at low lift of the North American YF-100A airplane at a range of Mach numbers as obtained with rocket-propelled models for an airplane, with the horizontal tail removed, and with wing removed conditions. Results regarding drag, longitudinal trim, longitudinal stability, and flutter and buffet are provided.

From Summary: "The methods of NACA reports 865 and 1090 have been applied to the calculation of the rolling-moment and yawing-moment coefficients due to rolling for unswept wings with or without flaps or ailerons. The methods are based on lifting-line theory and allow the use of nonlinear section lift data. The method presented in this report permits calculations to be made somewhat beyond maximum lift for wings having no twist or continuous twist and employing airfoil sections which do not display large discontinuities in the lift curves. Calculations can be made up to maximum lift for wings with discontinuous twist such as that produced by partial-span flaps or ailerons, or both. Two calculated examples are presented in simplified computing forms in order to illustrate the procedures involved."

This report focuses on the study of the stabilized pinch program made to increase the plasma temperature and improve the plasma conductivity and containment. One method proposed is the usage of a large toroidal stabilized pinch, which is described here.

This report discusses the problem of obtaining thermonuclear temperatures as part of reaching a controlled fusion reaction for fusion power. Tables covering radiation losses and thermonuclear reaction rates are included. Talk before JCAEC in Washington, D. C.