The aqueous corrosion behavior of defected fuel elements having a U-2 wt. % Zr core with Zircaloy-2 cladding has been studied. A standard diffusion heat treatment for 7 hours at 880 C, followed by moderately rapid cooling, was established to overcome the effect of subtle defects in 15-mil Zircaloy cladding. The development of this heat treatment was carried out primarily with small rod specimens, which were also used to obtain data on aurxiliary effects of thw diffusion heat treatment. The heat treatment has been applied to full diameter tubes. One of these tubes was tested with subtle defects and various sections have been observed following the insertion of gross defects. These observations have shown a difference in the rate of hydrogen evolution as a result of heat treatment. In addition, the heat treatment changes the nature of failure in both full diameter tube sections and small rods. The presence of 2 wt. % Zr in the core reduces the corrosion rate considerably. Comparative quantitative data are presented for uranium alloys with various zirconium contents up to 15 wt. %. (auth)

Since nuclear magnetic resonance ''chemical shifts'' are considered to be good measures of electron densities in molecules, the extent to which they can be correlated with the polarographic half-wave potentials of organic compounds has been surveyed. To extend the applicability and interpretation of the proposed correlation, parallel correlatioan of E, with Hammett's sigma and Taft's sigma parameters were made, since both of the latter are also regarded as indication of electronic distrinution at the reactive center. The data in general support the view that changes in half-wave potential with structure are due to both electronic and steric effects, as well as perhaps to adsorption phenomena. Significantly, NMR data obtained with one type of substituent could be correlated with E/sub 1/2 data for a similar type of substituent. New NMR data for aliphatic nitro and halogen compounds are reported. (auth)

S>Optical tooling has been evaluated for the measurement of physical dimensions of radioactive parts through hot cell windows. Instruments were set up outside of a four foot thick lead glass window and by means of a grid plate which had been accurately scribed, a ''contour map'' or calibration chart of the window variations was recorded. Although the window was not specially selected, the readings were within 1.0% of the true dimension without using correction factors. One of the calibration chart with the window reduced the error to plus or minus 0.1%. The method is considered feasible and sufficiently fast for a wide variety of hot cell measurements. A pin point light source is suggested as a simple check for selective assembly of lead glass laminates during manufacture of hot cell windows to provide control of optical properties. (auth)

The JOFIT code fits, by a least squares technique, the curve y = A J/sub o/STAB(x-C)! from 4 to 500 points of observed data, computing the parameters A, B, C and the standard deviation of the final values of A, B, C, i.e., S/sub A/, S/ sub B/, S/sub C/. It is also possible to investigate the error in a region about the final values of A, B, C by computing the sums of the squares of the residuals at a series of points in this neighborhood. Typical computing and editing time for a 50 point problem is 2 minutes. Any size IBM-704 computer is adequate, and drums and tapes are not used. (auth)

Data are presented on the absorption of molybdenum on activated carbon. The effect of retention time and linear flow on absorption, the use of sodium hydroxide as an eluant, and the possibility of recovering molybdenum from the caustic eluate are discussed. (auth)

Variations in the photofission cross section near ''threshold'' with initial kind of nucleus were investigated for seven spheroidal nuclei in the region of atomic numbers 90, 92, 93. The photofission cross sections at the two discrete energies 6.14 and 7.0 Mev were determined for the following even-even nuclide . Th/sup 232/, U/sup 234/, U/;sup 236/, and U/sup 238/; and also the odd- A nuclides. U/sup 233/, U/sup 235/ and Np/sup 237/. Nuclear excitation of the target nuclei was achieved via gamma rays from nuclear capture of protons on fluorine. Protons of 1.380- and 3.645-Mev energy impinged on a thick CaF/sub 2/ target. The highenergy quanta of 5.14, 6.91, and 7.12 Mev so obtained represent the well-known ground state transitions in O/sup 16/, whose relative intensities change with bombarding energy of the proton. The fission counting was done in a double-region ionization chamber of 2 pi geometry. The heavy-element samples were nearly uniform oxide deposits of about one mg/cm/sup 2/, on platinum. Employing the known thick target relative gamma-ray intensity ratio, I(6.91 + 7.12)/I(6.14), plus the measured gamma flux and fission counting yield at each of the two above proton energies, the ( gamma , fission) cross sections at 6.14 snd …

The results of temaperature measuring experiments conducted for Rainier shot, Operation Plumbbob are described, The temperature distribution in the surrounding tuff resulting from the detonation of an underground nuclear device yielding 1.7 kilotons of energy has been measured, Data indicate peak temperatures in the vicinity or 90 deg existing in the central regions which drop rapidly to approach ambient temperatures at distances of about l80 feet from the original ground zero, Based on measurements taken in three holes drilled into the central regions, contours of constant temperature are constructed The temperature picture is consistent with the consideration that most of the heat entered the water contained originally in the tuff and the unconsolidated material which filled the cavity after its initial collapse, The amount of energy contained in the central regions in the form of tuff heated to below 90 deg C is roughly estimated to be greater than one-half of the total energy release. An unsuccessful attempt to measure the temperature rise across the shock front of the pressure wave produced by the detonation is described, and reasons for failure are discussed. (auth) A slow chopper neutron velocity spectrometer was used to measure the energy spectrum of thermal neutrons …

The partial differential equations of the multigroup diffusion model of reactor physics are shown to have solutions both in the time-independent and timedependent problems, and the usually assumed behavior of these solutions is shown to be mathematically valid. The method of spectral representation is developed for the multigroup diffusion operator. (auth)

Memorandum presenting the effects of deflected inboard ailerons on the wing loads of a 45 degree sweptback wing-body combination in the 16-foot transonic tunnel. The model had a wing with an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections. Results regarding the chordwise pressure distributions, effect of ailerons on wing section loadings, effect of aileron on wing loading, and effects of a deflected aileron on opposite-wing loading are provided.

"A brief investigation of the longitudinal stability and control effectiveness at supersonic speeds of a model of a low-wing missile with interdigitated tail surfaces was made in the Langley Unitary Plan wind tunnel. The data were obtained at Mach numbers M of 2.29, 2.97, and 3.51 for Reynolds number (based on the mean geometric chord of the wing) of 1.15 x 10(exp 6), 1.14 x 10(exp 6), and 1.11 x 10(exp 6), respectively. Data were obtained for three settings of the longitudinal control surfaces: with deflection of all surfaces, with deflection of the lower surfaces only, and with all surfaces undeflected" (p. 1).

Effects of boattail area contouring and simulated turbojet exhaust on loading and fuselage-tail component drag of twin-engine fighter-type airplane model.

Report presenting an investigation conducted on the helicopter test tower to determine experimentally the low tip Mach number stall and high tip Mach number drag divergence characteristics of a helicopter rotor with an NACA 0009 tip airfoil section. Results regarding rotor hovering performance, rotor-blade pitching moments, rotor profile-drag torque, and a comparison with two-dimensional drag-divergence data are provided.

Report presenting testing in the high-speed 7- by 10-foot tunnel to investigate the high-subsonic static longitudinal stability characteristics and lift-drag ratios of several wing-body models designed to provide high lift-drag ratios at Mach number 1.4. The basic configuration had a thin highly swept wing of aspect ratio 2.91 with NACA 65-A series airfoil sections. Results regarding longitudinal stability, lift, drag, and lift-drag ratio are provided.

Report presenting an investigation to determine the effects of leading-edge radius and profile thickness on the oscillatory lateral stability derivatives for a series of delta wings with 60 degrees of leading-edge sweep. The wings were oscillated in yaw about their vertical axes. Results indicated that there were noticeable decreases in all the derivatives due to increase in leading-edge radius at angles of attack above approximately 12 degrees.

Report presenting a wind-tunnel investigation at low speeds to determine the flight characteristics of a model of a sweptback-wing jet-transport airplane equipped with an external-flow jet-augmented slotted flap. Results regarding the longitudinal stability characteristics, longitudinal control characteristics, lateral stability characteristics, and lateral control characteristics are provided.

Report presenting an investigation conducted in a turbojet engine mounted in a sea-level test stand to determine the vibrational characteristics of four representative types of air-cooled turbine blades.Two were standard-span blades and two were long-span blades for high mass-flow turbines. Results regarding the coolant-flow rate, vibratory stresses, vibrational characteristics, and failures are provided.

Report presenting a study in which the effective flow area of a convergent exhaust nozzle was reduced by injecting a high-pressure secondary jet into the nozzle near the exit. Analytical expressions relating the performance with significant design and operating variables were developed. Some of the configurations, altered to operate as jet deflectors, produced significant values of side force but also operated at reduced effective flow area.

Report presenting experimental results relating to the effect of pressure gradient on the location of transition for several constant-pressure-gradient models an two power-profile models. Results regarding the local flow conditions, recovery-factor distributions, effect of unit Reynolds number, and effect of pressure gradient are provided.

From Summary: "An analysis is given of the oscillatory motions of vehicles which traverse ascending and descending paths through the atmosphere at high speed. The specific case of a skip path is examined in detail, and this leads to a form of solution for the oscillatory motion which should recur over any trajectory. The distinguishing feature of this form is the appearance of the Bessel rather than the trigonometric function as the characteristic mode of oscillation."

Report presenting power spectral methods of analysis as applied to flight test measurements of the strain responses of a large swept-wing bomber airplane in rough air in order to determine the effects of airplane in rough air in order to determine the effects of airplane structural dynamics on the strain responses.

The charts presented give the compressive buckling coefficients for a single-truss-core and a double-truss-core sandwich plate. These charts cover a wide range of sandwich proportions and may be used for sandwiches with unequal faces. They apply to inplane compressive loads acting parallel or perpendicular to the core direction or for various combinations of these loads. (author).

Report presenting the emergence- and planing-spray characteristics of flat-bottom surfaces representing hydro-skis with various bow shapes and deflectors. The most favorable emergence spray was obtained with a bow of triangular plan form and sharp profile. Results regarding practical design considerations are also provided.

Note presenting compressive strength test results from room temperature to 1000 degrees Fahrneheit and compressive creep test results from 700 to 1000 degrees Fahrenheit for plates of 17-7 PH stainless steel, Condition TH 1050, which were edge-supported in V-groove fixtures. The combinations of average stress, temperature, and time that produce given amounts of creep strain or failure are shown on master curves which facilitate interpolation of the test results.

"Measurements of runway roughness obtained by a profile-survey method are presented. A variety of runway lengths or sections and degrees of roughness were measured. The results are presented as elevation profiles of the runways surveyed and in the form of power spectra" (p. 1).