Correlations of alpha-decay energies in terms of mass number and atomic number have been made for all of the alpha-emitting species now numbering over 100. For each element isotopes show increase in alpha-energy with decrease in mass number except in the region of 126 neutrons where there is an explainable reversal. This reversal has the effect of creating a region of relatively low alpha-energy and long half-life at low mass numbers for such elements as astatine, emanation, francium, and possibly higher elements as had been noted already for bismuth and polonium. Methods and examples of using alpha-decay data to define the energy surface in the heavy element region are discussed. The regularities in alpha-decay are used for predictions of nuclear properties including prediction of the beta-stable nuclides among the heavy elements. The half-life vs. energy correlations show that the even-even nuclides conform well with existing alpha-decay theory, but all nuclear types with odd nucleons show prohibited decay. The reason for this prohibition is not found in spin changes in the alpha-emission but in the assembly of the components of the alpha particle, and this theory is discussed further in terms of observations made on nuclides having two or more alpha-groups. …

This report is a document summarizing all information available on life aspects of various measures proposed to reduce or eliminate corrosion of Van Stone flanger.

Report discussing a method for the stepwise calculation of the number of transfer units utilized in a given solvent extraction operation. "Use of the method results in a very appreciable saving in time of calculation with an error of 1.5% for the runs tested. The error tends to become smaller with increasing total numbers of transfer units involved."

Physical and inorganic Chemistry. Studies are reported on: volatile complexes of ZrCl/sub 4/ and HfCl/sub 4/ with POCl/sub 3/; reaction of UCl/sub 4/ with LiAlH/sub 4/; preparation and properties of metal uranates and polyuranates; heats of solution of UO/sub 2/(NO/sub 3/)/sub 2/ hydrates; absorption spectra of Np in HClO/sub 4/, and separation of Np and Pu chlorides by a flow method. Process Chemistry. Extraction of Th from Mailiackrodt U raffinate was studied. Nuclear Chemistry aad Radiochemistry. Invesigations were carried out on: organic tritium; exchange reactions of U ions in solution; exchange reactions of Fe in aqueous solutions: Tc recovery from old Hanford slugs; (a,2n) cross section of Pa/sup 231/; and spontaneous fission counting U/sup 236/ and Pu/sup 238. (T.R.H) l822 Nuclear Chemistry and Radiochemistry. Measurements of the half- lives of Ac/sup 227/ and RaD(Pb/sup 210/) were continued. The effective pile neutron capture cross sections for U/sup 236/ were determined by measuring the activity of the resultant U/sup 237/ with an end window geiger counter. A study of ion chambers for tritium analysis is presented. Procedures were developed for the determination of tritium and C/sup 14/ in onganic compounds. Physical and Inorganic Chemistry. An investigation of the electrochemistry of Np in …

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Report presenting comparative tests of the rolling power of plain constant-chord, full-delta, and half-delta ailerons on delta wings with varying degrees of sweepback were tested on rocket-propelled test vehicles. Results regarding the effect of leading-edge sweepback, a comparison of rolling effectiveness, and comparison with theory are provided.

Report presenting the hydrodynamic characteristics of a swept planing-tail hull as determined by water tank testing. The hull shape was based on results from previous testing indicating that symmetrical airfoil sections and slender boom-like afterbodies lower the drag. Results regarding spray characteristics, take-off stability and trims, landing stability, resistance, and directional stability are presented.

Report presenting an investigation in the high-speed 7- by 10-foot tunnel to determine the high-subsonic aerodynamic characteristics of three different types of flying-boat hull: a planing-tail hull, a blended hull, and an airfoil-forebody swept hull.

Report presenting the results of flight tests showing lateral oscillation in the Bell X-1 and calculations created to determine the effects of changes in several mass and aerodynamic parameters on the lateral oscillations. Calculations indicate that lateral stability should be improved by a more positive inclination of the principal axis of inertia or a reduction of the value of yawing moment of inertia.

Report presenting the pressure-recovery characteristics of a model with two scoops situated on the aft position of a long forebody and connected through diffusors to a common settling chamber at a range of Mach numbers. The effects of interaction between the flow in the two air-induction systems and of varying the mass flow through the boundary-layer scoops were studied. Results at several different angles of attack are provided.

Report presenting an investigation at subsonic and transonic speeds in the high-speed 7- by 10-foot tunnel to determine the aerodynamic characteristics of a 42.7 degree sweptback wing with a 20-percent-chord and 50-percent-span outboard aileron. The investigation was performed in transonic flow over a bump on the tunnel floor and in subsonic flow on one of the tunnel side walls.

Report presenting an analysis of the effects of compressibility on the pressure coefficients of several bodies of revolution by comparing experimentally determined pressure coefficients with corresponding pressure coefficients calculated by the use of linearized equations of compressible flow. The results indicated that the theoretical methods predict the subsonic pressure-coefficient changes over the central portion of the body but do not predict the pressure-coefficient changes near the nose.

Report presenting a supersonic compressor design with supersonic velocity at the entrance of the stator on the assumption of two-dimensional flow. The rotor and stator losses assumed in the analysis are based on the results of preliminary supersonic cascade tests. The starting conditions and stability of the flow in rotor and stator are discussed, and the desirability of the variable-geometry stators and adjustable guide vanes is indicated.

"Four 90 degree two-dimensional turning passages designed by the method of characteristics were tested at an inlet Mach number of 1.71. The measured losses varied from 5 to 15 percent of the inlet stagnation pressure. The smallest loss was obtained for a passage in which separation on the convex surface was minimized through the introduction of a favorable pressure gradient" (p. 1).

Memorandum presenting measurements made in the transonic speed ranges of the static-pressure position error at a distance of 0.96 chord ahead of the wing tip of both the 8-percent-thick-wing and the 10-percent-thick-wing X-1 airplanes, and at a point 0.6 maximum fuselage diameter ahead of the fuselage nose of the X-1 airplanes. Results regarding the accuracy of pitot-static heads, static-pressure error of wing-tip installation, static-pressure error of the fuselage-nose installation, and error in total pressure are provided.

Tests were made to determine the straight run limitations of the Beth-Flo Gentile Flow Tube. The effect of surface roughness on tube performance was also investigated. The permanent head loss of the tube was determined.

The following report describes the design and construction of the reactor building wing, designed to attach to the reactor building for the Argonne National Laboratory.

Report discussing a study with the following objectives: "to synthesize pure specimens of both methylisoproplydiketone and 1,1 dinitroisobutane, to determine their physical and chemical properties, and to devise analytical methods which permit their quantitative determination in hexone-nitric acid systems to be encountered in the Redox Process."

A supplementary investigation on the stabilization of the Jettisonable nose section of the X-2 airplane has been conducted in the Langley 20-foot free-spinning tunnel. It was found that the nose section could be stabilized by the addition of curved fins which could be folded against the fuselage for normal flight.

"A supersonic compressor design having supersonic velocity at the entrance of the stator is analyzed on the assumption of two-dimensional flow. The rotor and stator losses assumed in the analysis are based on the results of preliminary supersonic cascade tests. The results of the analysis show that compression ratios per stage of 6 to 10 can be obtained with adiabatic efficiency between 70 and 80 percent. Consideration is also given in the analysis to the starting, stability, and range of efficient performance of this type of compressor" (p. 1).

Report presenting a survey of the present status of research on boundary-layer control and its possible applications in aeronautics. The applications considered include reduction of profile drag by the elimination of turbulent separation, increase of the maximum lift coefficient through control of separation, use of suction and blowing slots near the trailing edge of the airfoil as a means of lateral control, use of boundary-layer control as a means of increasing the efficiency of diffusers and bends, and the use of boundary-layer control to influence shock-boundary-layer interaction at high speeds.