Report presenting a wind tunnel investigation to determine the downwash angles, dynamic pressure loss, and wake width behind wings with sweep angles of 45, 30, and 0 degrees. Results indicated that the spanwise distribution of downwash was affected by sweep in a manner similar to span loading, increased toward the root by sweepforward and toward the tip by sweepback.

Report presenting an investigation to determine the benefits obtainable by applying boundary-layer control to a 45 degree swept-forward wing-fuselage combination. Force and pressure-distribution data were obtained with and without boundary-layer control with various combinations of leading-edge and trailing-edge flaps.

Report presenting the aerodynamic characteristics of an all-movable, triangular-plan-form wing alone and with a body as determined from semispan model tests. The agreement between calculated and experimental results was not satisfactory for the most part, which seemed to be due to the failure of linear theory to define the actual flow field about the configurations investigated. Results regarding lift characteristics, drag characteristics, and pitching-moment characteristics are provided.

Report presenting an investigation in the supersonic tunnel at Mach number 1.85 and angles of attack from 0 to 5 degrees to determine optimum design configurations for a convergent-divergent type of supersonic diffusers with a subsonic diffuser of 5 degrees included divergence angle. Total-pressure recoveries in excess of the theoretical recovery across a normal shock at a free-stream Mach number of 1.85 were obtained with a number of configurations.

Report presenting an investigation of a wing-body combination with a plane triangular wing of aspect ratio 4 and NACA 0005-63 sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.

Report presenting testing of a wing-body combination with a plane triangular wing of aspect ratio 2 and NACA 0003-63 sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.

"A wing-body combination having a triangular wing of aspect ratio 4 with NACA 0005-63 thickness distribution in streamwise planes, and cambered and twisted for a trapezoidal span distribution has been investigated at both subsonic and supersonic Mach numbers. The lift, drag, and pitching moment of the model are presented for Mach numbers from 0.25 to 0.96 and 1.20 to 1.70 at a Reynolds number of 1.5 million. The variations of the characteristics with Reynolds number are also shown for several Mach numbers" (p. 1).

The gust and draft velocities from records of NACA instruments installed in P-61C airplanes participating in thunderstorm flights at Clinton County Army Air Field, Ohio, from August 13, 1947 to August 15, 1947 are presented.

Wind-tunnel tests at low Mach number of a Republic F-84C airplane were conducted to determine by pressure-distribution measurements the air loads on wing-tip tanks and the change in wing load distribution due to the presence of tip tanks. Measurements of the aeroelastic twist of the wing were also obtained. Results are presented in the form of loading coefficient, center-of- pressure location, pitching-moment coefficient, aerodynamic-center location, and aeroelastic twist. The investigation revealed that the redistributions in loading brought about by either the tip tanks or elastic deformation of the wing were relatively small when compared with the chnnges in loading normally associated with the deflection of an aileron.

From Introduction: "Afterburning is well established as an effective means of increasing the thrust of a turbojet engine. In order to obtain the maximum thrust from an afterburner, it is necessary to burn to the highest temperatures possible (reference 1). At these high temperatures, material limitations (reference 2) necessitate the installation of cooling systems to permit safe and reliable operation."

Report presenting an experimental investigation of external airfoils, known as paddle-control surfaces, as the longitudinal control device on a triangular wing of aspect ratio 2. The lift, drag, pitching moment, and hinge moment were obtained for a variety of Mach numbers.

Report presenting a comparison of the hydrodynamic impact loads and motions encountered in testing a V-step and a transverse-step flat-bottom hydro-ski with beam loadings of about 4.5. Testing occurred in smooth water over a range of velocities, flight-path angles, and fixed trims. Results regarding time histories of draft, vertical velocity, and vertical acceleration, impact lift coefficient, draft coefficient, and time coefficient for rebound are provided.

Report discussing an investigation to determine the effects of changes in aspect ratio and tail height on the longitudinal stability characteristics of a model with a 32.6-degree sweptback wing. The effects of a leading-edge discontinuity were also examined.

From summary: This report describes the 10-watt Sr-90 thermoelectric generator, the dc-to-dc converter, batteries and the method of installation in the light buoy.

Quarterly report describing the progress and development of improved zirconium alloys for service in superheated water and steam. This report covers the period between October 1 to December 31, 1960 and was conducted by the United States and the European Atomic Energy Community (EURATOM).

Report discussing an experiment testing the severity of attack of an aluminum slug jacket containing one or more spots hotter than the rest of the jacket. These conditions match those likely to exist in a poorly bonded slug.

The distribution coefficients of Pu(VI) and Pu(III) have been measured as a function of the TTA, hydrogen ion, and nitrate ion concentrations in the TTA-benzen-nitric acid system. The extraction constants for Pu(VI) and Pu(III) are 1.4 X 10(-2) and 2 X 10(-5), respectively.

Discussing drilling recommendations for Dry Valley, in San Juan County, Utah

The compilation, assessment, and expansion of the Strong Earthquake Ground Motion Data Base.

The usual method of removing surface oxide from plutonium metal samples, by electrolytic cleaning in a mixture of ethylene glycol and phosphoric acid, is not satisfactory for preparing samples for oxygen determination. Samples prepared in this way give erratic oxygen values. This report describes a new method of electrolytic cleaning, using a 20 ~ aqueous potassium carbonate solution as the electrolyte. The sample is placed in a rotating tantalum cup which is made the anode. Electrolysis for two minutes at 4.5 volts is usually sufficient. Samples cleaned by the new method give lower and more consistent oxygen results than those prepared in the old way. The new method is also neater and more convenient.

The purpose of this study was to develop and design a cutting torch which would slit aluminum tubes in a graphite matrix without damaging the graphite.

The method of dispersion relations has in recent years found a wide application for the study of elementary particle reactions. Most of the work, however, deals with reactions of the type [formula], while the theory of those with more than two particles in the final state is still in a very preliminary stage. One reason for this is that even with only three particles in the final state the theory is already much more complicated. Nevertheless, a further development of the theory seemed to us very desirable. The theory at present is being developed on various levels simultaneously. Generally speaking, the aim of this paper is to put the theory in a form as closely as possible analogous to Mandelstam's formulation of the theory of reactions of type [formula]. In the later sections we specialize on reactions [formula], but as much as possible the formulation is in more general terms.

This paper describes the method developed and the results obtained in an extensive program of measurement of the masses of charged pions. Measurements were made of the total ranges in nuclear track emulsion and the momenta (obtained from the curving of the particle trajectory in the magnetic field of the 184-inch cyclotron) of pions and protons of nearly the same velocity.

Computer printout listings of three data tables (Digitized Accelerogram, Recording Station, and Earthquake) organized alphabetically by country.