From introduction: "At the request of WAPD, a study has been made of the effect of minor compositional variables on the corrosion behavior of uranium-molybdenum alloys in 650 F degassed water."

Report presenting simulator studies of a homing missile pursuing a constant-velocity nonmaneuvering target. The missile dynamics in pitch and roll, seeker method of deflection and control, and the missile-target geometry were simulated to determine whether the method of control and detection in conjunction with the missile dynamics were feasible.

Report presenting flight tests using a rocket-propelled 60 degree delta-wing body configuration, which included a NACA 0003-63 wing airfoil section. Drag at lift and stability data were obtained for a range of Mach numbers.

From Summary: "A method of computing span loads and the resulting rolling moments for sideslipping wings of arbitrary plan form in incompressible flow is derived. The method requires that the span load at zero sideslip be known for the wing under consideration. Because this information is available for a variety of wings, this requirement should not seriously restrict the application of the present method. The basic method derived herein requires a mechanical differentiation and integration to obtain the rolling moment for the general wing in sideslip."

Memorandum presenting an experimental investigation of the adaptation of a transonic slotted tunnel to supersonic operation by enclosing the slots with fairings. The adaptation allows the extension of peak Mach number of the tunnel to be made at a reasonable cost in both time and effort, provided simplicity and ease of installation are taken into consideration during the design of the cover fairings. The nozzle is found to be sensitive to phenomena that will cause thickening of the boundary layer in the slot cover fairing.

Report discussing testing in the low-turbulence tunnel to determine the effectiveness of several configurations of vortex generators in increasing maximum lift of a 6-percent-thick symmetrical circular-arc airfoil section. None of the configurations tested were found to greatly increase the lift. Some of the configurations tested included a single row of vortex generators, two rows of generators, larger vortex generators, and sweeping forward the front row of generators.

Report presenting a free-flight investigation of a rocket-powered control research model to determine the force and hinge-moment characteristics of a half-delta tip control on a delta wing. Results regarding the control hinge moments, control normal force, and total normal force are provided.

Report presenting an investigation of the planing characteristics of various combinations of a wheel and a hydro-ski. Models tested included at least two values of the following parameters: diameter of wheel, width of wheel, cross-section shape of wheel, fore-and-aft location of wheel, lateral location of wheel, gap between wheel and ski, rotation of wheel, and protrusion of wheel. Results regarding the general effect of a wheel, effect of wheel shape and size, effect of wheel-ski arrangement, and possible methods of reducing resistance are provided.

Report presenting tests in the 11-inch hypersonic tunnel at Mach number 6.86 to determine the effectiveness of an adjustable supersonic diffuser without boundary-layer control in reducing the pressure ratios across the system required to maintain supersonic flow. Testing indicated that the pressure ratio could be reduced to about one-third the pressure ratio required for starting.

Report presenting a flight investigation of a small, all-movable tail to determine whether it is an effective longitudinal control for a cruciform, delta-wing missile at a range of Mach numbers from 0.67 to 1.81. The stability, control, hinge-moment, and drag characteristics are provided.

An investigation of the performance characteristics of annular-diffuser designs applicable to turbojet afterburners. The best vortex-generator installations improved the diffuser static-pressure rise and downstream radial distributions without significantly altering the loss coefficients. Results regarding the axial inlet flow and whirling inlet flow are provided.

Equations are presented for the attenuation characteristics of single-chamber and multiple-chamber mufflers of both the expansion-chamber and resonator types, for tuned side-branch tubes, and for the combination of an expansion chamber with a resonator. Experimental curves of attenuation plotted against frequency are presented for 77 different mufflers with a reflection-free tailpipe termination. The experiments were made at room temperature without flow; the sound source was a loud-speaker. A method is given for including the tailpipe reflections in the calculations. Experimental attenuation curves are presented for four different muffler-tailpipe combinations, and the results are compared with the theory. The application of the theory to the design of engine-exhaust mufflers is discussed, and charts are included for the assistance of the designer.

Memorandum presenting an investigation of the dynamic stability of the Bell X-5 research airplane at 58.7 degrees sweepback and at altitudes of 40,000 feet and 25,000 feet over a Mach number range of 0.5 to 0.97. The results show that the longitudinal oscillatory motions are well damped over the entire Mach number range except for residual oscillations resulting primarily from engine gyroscopic coupling with the lateral oscillatory mode. The longitudinal and lateral frequency-response characteristics were obtained and some coupling effects were noted.

From introduction: This report summarizes a study of the composution and physical properties of a number of hydrocarbon diluents together with some generalizations regarding relations between [vapor pressure, density and viscosity] properties.

A two and one-half year period of extreme caution where titanium and nitric acid are involved has passed since the occurrence of the last and most serious uncontrolled incident involving titanium and nitric acid. During this period controlled explosions involving titanium and nitric acid have been routinely reproduced, additional laboratory and pilot plant experience has been gained and successful industrial applications have been appraised. Based on laboratory data and the known industrial experiences, it is concluded that titanium can be safely employed in systems handling nitric acid that contains more than two (2) percent water. It is recommended that the titanium heat exchanger recently fabricated by the Technical Shops be installed in the Purex Plant plutonium concentrator when replacement of the stainless steel unit now in service becomes necessary.

New reactors presently in design or construction stages, as well as revised operating procedures for existing reactors, have shown an increasing emphasis on extending the exposure time of the reactor fuel elements. However, operating experience at Hanford, as at other installations, has demonstrated that as the amount of burn-up in uranium metal is increased an increase is also noted in operational difficulties resulting from the dimensional behavior of the fuel. During reactor irradiation uranium slugs or rods have been observed to change in length and diameter, to warp, and to develop surface roughening.

Consider an orthogonal series [formula] where [formula] is an arbitrary orthonormal system for the interval (a, b) and [formula] is a sequence of real numbers. This report is a collection of theorems which give sufficient conditions for the convergence almost everywhere in (a, b) and summability a. e. in (a, b) of the above series.

Memorandum presenting tests of two rocket-powered models of a 45 degree swept-wing airplane configuration with different underwing fuel-tank installations located at approximately half the wing semispan. Results of the tests were compared with previously reported data from a similar configuration with no tanks and with isolated tank data. These results include trim, buffeting, drag, and static longitudinal stability are provided.

Photogeologic map of the Orange Cliffs-4 quadrangle, Wayne County, Utah

A method of determining enclosure pressure in the event of a reactor rupture is presented and a sample calculation is shown. This method was used in calculating the design pressure of the Dresden Nuclear Power Station enclosure.

The description of the thick-target neutron yields from the D(t,n)He4 and the D(d,n)He3 reactions is calculated as a function of the energy of the bombarding particles. For 60-kev particles the ratio is 108. I increases to 168 at 100 Kev and to 194 for 120-kev particles. A qualitative discussion of the yields from various deuterium target leads to the conclusion that the greatest yield would come from the target which has the lowest stopping cross section per deuterium atom.