From abstract: "A scintillation detector has a pulse height output which is a linear function of the energy of impinging gamma radiation. A pulse height analyzer system determines the amplitude distribution of this train of pulses. The system also displays this information graphically in a form which is convenient for further analysis."

Quarterly progress report describing work related to a study of radiation physics problems involved in the design of high-level cesium-137 gamma sources. It outlines work completed and ongoing goals for the project.

This report studies tritium oxides and tritium in water vapor, a product of P-10.

Abstract. a method of recovering thorium from slag from the bomb process of producing thorium has been developed. HCl and NaOH are the only chemicals required in quantity. Materials required for a representative slag are given.

Report presenting the results of a wind-tunnel investigation to determine the effects of a variation in wing taper ratio on the longitudinal characteristics of a wing-body combination at a variety of Mach numbers. The wings had an aspect ratio of 3, an unswept midchord line, and an NACA 64A003 profile. Results regarding the lift and pitching-moment characteristics and drag characteristics are provided.

Report presenting a summary of NACA research on afterburners for turbojet engines during the past 5 years. The references present over 1000 afterburner configurations and about 3500 hours of operation. The report covers the following topics: burner-inlet diffusers, fuel-injection systems, flameholders, combustion space, combustion instability, starting and transient performance, effects of diluents, and burner-shell cooling.

Report discussing testing on the drag, longitudinal stability, and lateral stability characteristics of a model of the McDonnell F4H-1 airplane. The minimum drag coefficients, neutral point, horizontal-tail-incidence range, static directional stability, and effective dihedrals are presented.

Report presenting an investigation of zero-lift drag of a fin-stabilized wing-body combination from high-subsonic to supersonic speeds in a range of Reynolds numbers. The wing was unswept about the 74.5-percent-chord line, an aspect ratio of 3.04, a taper ratio of 0.394, and 4.5-percent-thick modified hexagonal airfoil sections. Results regarding total drag, wing-plus-interference drag, and base pressure are provided.

"The influence of triangular-shaped end plates on the lift and the flow field of a canard-type control surface mounted on a symmetrical fuselage was investigated in the Lewis 8- by 6-foot supersonic wind tunnel at a Mach number of 2.00, body angle of attack of 2 degrees, and control-surface deflection angles of 3 degrees, 6 degrees, 8 degrees, and 10 degrees. The investigation demonstrated that the addition of end plates to a canard-type control surface increased its lift and rearranged the single vortex into a two-vortex system. Perforating the end plates reduced these effects and resulted in a decrease in lift and a change in the flow-field characteristics" (p. 1).

Force and pressure-recovery characteristics of a nacelle-type conical-spike inlet with a fixed-area bypass located in the top or bottom of the diffuser are presented for flight Mach numbers of 1.6, 1.8, and 2.0 for angles of attack from 0 degrees to 9 degrees. Top or bottom location of the bypass did not have significant effects on diffuser pressure-recovery, bypass mass-flow ratio, or drag coefficient over the range of angles of attack, flight Mach numbers, and stable engine mass-flow ratios investigated. A larger stable subcritical operating range was obtained with the bypass on the bottom at angles of attack from 3 degrees to 9 degrees at a flight Mach number of 2.0. At a flight Mach number of 2.0, the discharge of 14 percent of the critical mass flow of the inlet by means of a bypass increased the drag only one-fifth of the additive drag that would result for equivalent spillage behind an inlet normal shock without significant reductions in diffuser pressure recovery.

Memorandum presenting testing of an NACA 65(sub 06)A004 airfoil to determine the effects of a solid-strip spoiler on buffeting forces. Fluctuations of both section normal-force coefficient and of section pitching-moment coefficient are presented as functions of angle of attack and of section normal-force coefficient. Generally, the spoiler decreased the fluctuating section normal-force and pitching-moment coefficients if comparison is made at constant angle of attack and increased these coefficients if comparison is made at constant section normal-force coefficient.

Report presenting studies of the final attack phase of an automatically controlled interceptor in flight and electronic simulators to investigate various airplane command and stabilization networks and to develop simple but adequate simulation techniques for the synthesis of automatic control systems. Results regarding automatic control with a simple command system, automatic control with the improved command system, and evaluation of the automatic control system in typical final attack maneuvers are provided.

Report presenting an experimental investigation to assess the effects of sweep and taper ratio on the longitudinal characteristics of a wing-body combination at a range of Mach numbers. The results indicated that increased leading-edge sweep caused a progressive decrease in lift-curve slope and the variation of Mach number of the lift-curve slope and static longitudinal stability. Results regarding the effect of sweep, effect of taper ratio, and comparison with results of a previous investigation are provided.

Report presenting an investigation in the transonic blowdown tunnel at Mach numbers from 0.63 to 1.41 to determine increments in lift, drag, and pitching moment of a sweptback semicircular air inlet installed in the root of a 45 degree sweptback wing. Results regarding internal pressures and inlet performances are provided.

Report presenting testing of two beams of three web types which were loading in bending and subjected to rapid skin heating at rates from about 50 to 70 degrees Fahrenheit per second. The investigation was meant to determine some of the effects that rapid skin heating would have on the buckling and failing strength of multiweb-wing structures. The three types of web tested included the channel web, corrugated web, and truss web.

From introduction: "This article constitutes the third of a series of three papers on the "direct" measurements of the meson masses by the "Hp vs. Range" mass ratio method...The study here reported is a logical extension of the pion-proton mass ratio technique."

The following report analyzes results from studies made while applying chelating agents to ion exchange separations of the elements americium and curium.

Abstract: "A description of the demand computer and its functions is given. Methods of testing and adjusting, and gain and response curves for the system and its parts are included."

The design of the present time of light mass spectrograph is similar to that of the isotron devised some time ago for isotope separation. The spectrograph will employ the time of flight principle only for the isotopic analysis of small samples.

Abstract: Both direct and coincidence counting apparatus are described. The elimination of cosmic ray events by coincidence plus gamma ray shielding permits the reduction of counting rates far beyond that obtainable with shielding alone. By selection of materials and development of new components and techniques, the residual background count of beta counting equipment can be reduced to a very low value. Geiger counter equipment for routine laboratory measurements is described, have a background count of 0.7 c/m. Scintillation counters are shown to have a background of 0.2 c/m at 30% efficiency. A portable Geiger counter with a 3.7 c/m background is also described.

Abstract: This report presents metallurgical .analyses and corrosion tests conducted to determine :causes of failure of two SM- 1 reactor vessel studs due to fracture in the threaded areas, after 23 months' operation (March 1959). Conclusions of corrosion tests are: (1) failure of the studs was caused by stress corrosion cracking, (2) contributing factors to failure of the studs were improper control of heat treatment of the studs and absence of treatment for stress relief after thread grinding operation.

From abstract: "Fuel materials proposed for use in the Advanced Test Reactor were evaluated."

"This report covers fire tests conducted on an experimental design of a wooden-jacket shield for radioisotope shipping containers" (p. i).

Memorandum presenting an investigation of the effects of stator cone angle and tip leakage on turbine performance. A single-stage turbine with 40-percent reaction was operated with two stators and two stationary shrouds. The turbine was operated at an entrance temperature of 660 degrees R with total-pressure ratios from 1.25 to 3.70 and equivalent mean blade speeds from 166 to 655 feet per second.