Preliminary recommendations are presented for drilling the area on a 1,000-foot grid to provide final elevation of the East Carrizo mining district.

Report presents the results of an investigation conducted to determine the effectiveness of liquid-cooling films on the inner surfaces of tubes containing flowing hot air. Experiments were made in 2- and 4-inch-diameter straight metal tubes with air flows at temperatures from 600 degrees to 2000 degrees F. and diameter Reynolds numbers from 2.2 to 14 x 10(5). The film coolant, water, was injected around the circumference at a single axial position on the tubes at flow rates from 0.02 to .24 pound per second per foot of tube circumference (0.8 to 12 percent of the air flow). Liquid-coolant films were established and maintained around and along the tube wall in concurrent flow with the hot air. The results indicated that, in order to film cool a given surface area with as little coolant flow as possible, it may be necessary to limit the flow of coolant introduced at a single axial position and to introduce it at several axial positions. The flow rate of inert coolant required to maintain liquid-film cooling over a given area of tube surface can be estimated when the gas-flow conditions are known by means of a generalized plot of the film-cooling data.

Map showing uncontrolled structure contours of the Beclabito Dome Area, Shiprock District, Arizona-New Mexico. The Salt Wash-Bluff contact was spotted on aerial photographs as a basis for the construction of the uncontrolled structure contour map

Report presenting preliminary results of one phase of a control-motion study program using data obtained from 276 maneuvers performed using a McDonnell F2H-2 jet fighter airplane during normal squadron operational training. Results regarding classification of maneuvers, airspeed, load factors, sideslip angle, and maximum pitching-, rolling-, and yawing-angular-acceleration variations with indicated airspeed are provided.

Report presenting an investigation of the two-dimensional aerodynamic characteristics of several NACA airfoil sections at four Reynolds numbers. Results regarding the minimum drag, maximum lift, lift-curve slope, and angle of zero lift and pitching moment are provided.

Report presenting a wind-tunnel investigation to explore the merits of split and chord-extension flaps on a 45 degree sweptback wing. Testing occurred at low speed on a semispan model equipped with split flaps of 60 and 90-percent span and a full-span chord-extension flap. Results regarding split flaps, chord-extension flap, and resultant lift coefficients after balancing pitching-moment coefficients are provided.

Technical report includes three reports of research progress: 1)Neutron scattering by A. Bratenahl; 2) Nuclear Cross Sections, Norman Knable.

From introduction: "Due to the hydrogen overvoltage at the surface of a mercury cathode, uranium solutions is hydrochloric acid may be reduced not only to the tetravalent state, but until considerable trivalent uranium is formed. Other metallic ions act as oxidation-reduction catalysts as well as being reduced themselves. The following paper is a study of the various reactions taking place in solution and at the surface of the cathode."

Abstract. A method for the preparation of beryllium oxide of high purity is presented. Beryllium basic acetate (BeO-3Be(C2H3O2)2) is prepared from the metal or a convenient salt, a chloroform solution of this material extracted with redistilled water, the dried basic acetate distilled in a quartz apparatus, and this purified material converted to the oxide by fuming down with sulfuric acid and igniting at 1000 degrees C. Impurities detectable spectrographically were reduced to a very low level.

Warping of a rod by a variation in heat transfer coefficient around the periphery is considered. Estimates for some simple cases are given, and a more precise numerical calculation is carried out in ne instance.

Measurements made in a uranium cylinder result in a mean value of 1.55 cm. for the diffusion length L for distances of 1 to 4 cm. from the base of the cylinder. Calculations give a value which agrees with the experimental result and show further that L increases from 1.40 to 1.63 cm. as the neutrons diffuse a distance of 5 cm. into the uranium.

"Values of the circulation function have been obtained for dual-rotating propellers. Numerical values are given for four, eight, and twelve-blade dual-rotating propellers and for advance ratios from 2 to about 6. In addition, the circulation function has been determine for single-rotating propellers for the higher values of the advance ratio. The mass coefficient, another quantity of significance in propeller theory, has been introduced" (p. 35).

"The solution of Von Karman's fundamental equations for large deflections of plates is presented for the case of a simply supported rectangular plate under combined edge compression and lateral loading. Numerical solutions are given for square plates and for rectangular plates with a width-span ratio of 3:1. The effective widths under edge compression are compared with effective widths according to Von Karman, Bengston, Marguerre, and Cox and with experimental results by Ramberg, Mcpherson, and Levy" (p. 1).

"Experimental results on the effect of the length-diameter ratio of the orifice on the spray characteristics, together with a brief analysis of the factors affecting these characteristics, are presented in this report. The length-diameter ratios tested ranged from 0.5 to 10; the orifice diameters from 0.008 to 0.040 inch; and the injection pressures from 2,000 to 8,000 pounds per square inch. The density of the air into which the fuel was discharged was varied from 0.38 to 1.35 pounds per cubic foot" (p. 79).