Abstract: "Creep and creep-rupture tests were made on 25-O aluminum sheet at temperatures of 500 and 550 C. The estimated stresses that will produce 0.5 per cent deformation and rupture in 10,000 hours at 400, 450, 500, and 550 C (data at 400 and 450 C are from BMI-T-29, dated June 9, 1950) are presented."

"This symposium is concerned with the basic aspects of radiation effects. When we turn to the genetic effects of radiation in mammals, there are so few aspects on which there is any information that the problem of sorting out the fundamental findings has hardly arisen. In this paper it will, therefore, be possible to survey most of what is known and pass on to a consideration of what is needed next. Since one of the purposes of this symposium is an interchange of views between investigators in different fields, an attempt will be made to avoid technical details. Among the practical needs in mammalian radiation genetics is a pressing one for more data on which to base estimates of the genetic hazards of radiation in man. The present paper will be concerned largely with this problem. Our own work is directed primarily in this direction, our objective being to uncover some of the basic facts in at least one mammal-the mouse. Before discussing the experimental work, however, it seems desirable to consider some of the general features of the genetic hazard of radiation."

From abstract: "A full-scale, always-safe, metal dissolver for Experimental Breeder Reactor fuel was designed, built, and installed for test operation. It was found that the dissolver operated satisfactorily, and feasible operating procedures were established for the dissolution of bare, or jacketed, EBR slugs. Minor modifications of the dissolver design have been required to accomodate [sic] a modified EBR slug, but it is believed that this will not significantly affect its operating characteristics."

Summary: "The laboratory data collected during the metallurgical evaluation of these rods indicate that lower rolling temperatures increased the ultimate and yield strength, the amount of cold work, and the degree of preferred orientation existing in these uranium rods."

Abstract: "A batch of slugs is being prepared for which the U-235 content will be 1.75 per cent, and it is of interest to calculate the minimum number of such slugs required for a critical assembly in water. Using Handbook (CL-697) methods, a critical assembly of these slugs arranged in a lattice with a spacing of 5.5 cm."

The following report deals with the application of the water boiler neutron source to the exponential experiments in an attempt to speed up lattice testing measurements.

Introduction: Studies of uranium-vanadium occurrences in the Four Corners region show that, with the exception of the Lukachuai area, all of the major deposits in the Morrison formation are grouped around the various igneous masses which are scattered irregularly throughout the Colorado Plateau. The pattern of deposition varies from mountain group to mountain group and each will be described separately. Maps accompany this report to supplement the descriptions of ore occurrences in the vicinity of the La Sal, Abajo, Carrizo, and Henry mountains. Elsewhere, it is believed that a written description will suffice.

Report presenting an investigation at Mach number 1.91 to determine the gross spreading characteristics of jets expanding from convergent and convergent-divergent nozzles using total-temperature surveys. Results regarding the preliminary development and jet spreading characteristics of the different types of nozzles are provided.

Performance characteristics of a two-dimensional isentropic diffuser have been experimentally determined at a Mach number of 3.85. At zero angle of attack, a maximum total-pressure recovery of 0.41 was obtained with a supercritical mass-flow ratio of 0.95. As a consequence of the twin-duct arrangement of the diffuser, a large discontinuity in pressure recovery and mass flow with a characteristic hysteresis was encountered between critical and subcritical operation. An asymmetric shock pattern with large-scale separation and flow reversal in one of the passages occurred at reduced mass flows. Pressure and force data presented for an angle-of-attack range from zero to 4 degrees.

Report discussing testing of a rocket-propelled airplane configuration model and a drag model, each with a 60 degree swept wing of aspect ratio 2.24, and different fuselages, at a Mach number range of 0.75 to 1.50. Information about the longitudinal stability, control, and drag characteristics and minimum-drag characteristics is presented.

Report presenting the zero-lift drag of a sweptback wing and body combination with nacelles with NACA 1-50-250 nose inlets locate in the wing tips as determined by flight tests of rocket-powered models at transonic speeds. Results regarding the pressure recovery and the effect of the nacelles on it are also provided.

Report presenting an investigation in the low-turbulence pressure tunnel at Mach number 1.2 to determine lift, drag, and moment characteristics of a wing with an airfoil section designed for maximum lift at low speeds, 45 degrees of sweepback, aspect ratio 4, and taper ratio 0.6. A similar wing with the NACA 65A006 airfoil section was also investigated and compared to the experimental wing.

Memorandum presenting minimum spark-ignition engines at reduced pressures for ethane, ethylene, acetylene, n-hexane, cyclohexane, and benzene.

From Introduction: "Analyses of heat transfer for liquid metals flowing turbulently in smooth tubes (low Pradtl numbers) are given in reference 1 and 2. The predicted heat-transfer coefficients from these analyses are considerably higher than those determined in the experimental heat-transfer investigations for mercury and lead bismuth given in references 2 to 4. If the analytical and experimental results for flow of gases are compared at low Peclet numbers, they are also found to be in disagreement (references 5 and 6)."

From Summary: "Force characteristics determined from tank tests of a 1/5.78-scale model of a hydro-ski-wheel combination for the Grumman JRF-5 airplane are presented. The model was tested in both the submerged and planing conditions over a range of trim, speed, and load sufficiently large to represent the most probable full-size conditions."

Memorandum presenting an investigation at a Mach number of 1.62 in the 9-inch supersonic tunnel of a series of missile configurations with tandem lifting surfaces of low aspect ratio and of nearly equal span. Some of the variables investigated were interdigitation angle, wing and tail plan form, and longitudinal location of wing with respect to tail. Lift, drag, and pitching-moment data are presented, together with center-of-pressure locations and tail-lift efficiency factors.

Report presenting a wind-tunnel investigation to determine the effects of two wing-root leading-edge plan-form modifications, including a notched leading-edge fillet and a rounded leading-edge fillet, on the low-speed longitudinal stability characteristics of an airplane model with a 50.7 degree sweptback wing. Results regarding stability at zero lift, variation of stability with lift coefficient, and lift and drag characteristics are provided.

Report presenting a low-speed investigation of the static longitudinal aerodynamic characteristics of a twisted and cambered wing with 45 degrees of sweepback and an aspect ratio of 8.0 in the 19-foot pressure tunnel. Testing included the effects of leading- and trailing-edge flaps, flow control fences, and a fuselage. Report presenting longitudinal stability characteristics, lift characteristics, drag characteristics, fuselage effects, Reynolds number effects, effect of wing roughness are provided.

Report presenting an investigation at transonic speeds to determine the control characteristics of a linked flap and spoiler. The control consisted of a linked combination of a quarter-span inboard plug-type spoiler and a full-span flap. Results regarding the hinge-moment, pitching-moment, lift, and rolling-moment are provided.

"A summary and analysis have been made of the results of various investigations to determine the aerodynamic characteristics of a supersonic aircraft configuration. The configuration has a wing with 40 degree sweepback at the quarter-chord line, aspect ratio 4, taper ratio 0.5, and 10-percent-thick circular-arc sections normal to the quarter-chord line. Experimental data were available for a Mach number range from 0.16 to 2.32. Results obtained from wing-flow, rocket-model, transonic-bump, and tunnel tests are presented and, where possible, are supplemented by empirical and theoretical calculations" (p. 1).

Report presenting information regarding transient oscillations observed in response to elevator pulses of the Douglas D-558-I airplane at a range of Mach numbers and altitudes. An application of the Fourier transform was used to obtain the frequency-response characteristics. The effects of lift coefficient on the frequency response are also included.

It is demonstrated that the temperature profiles of jets expanding into a supersonic stream are considerably smaller than the temperature profiles of jets expanding into quiescent air. The effect on the wake of varying afterbody geometry is shown to be small. The gross spreading characteristics of jets expanding from convergent and convergent-divergent nozzles in the base of a body of revolution with various boattail configurations at a Mach number of 1.91 are presented.

Memorandum presenting an investigation made at Mach numbers of 1.62 and 1.93 to determine the lift effectiveness and average downwash characteristics of several in-line missile configurations with rectangular and triangular tail plan forms. Breakdown tests were made for combinations of a body and four wing plan forms and two tail plan forms. Results regarding lift and drag results, pitching-moment results, and integrated downwash effects are provided.

Report presenting an investigation to determine the low-speed lateral characteristics of a triangular-wing airplane model. The model consisted of an aspect ratio 2 triangular wing in combination with a fuselage of fineness ratio 12.5, a thin, triangular, vertical tail with a constant-chord rudder, and a thin, unswept, all-movable horizontal tail.