"An analysis was made at flight Mach number of 0.9 to estimate performance of nuclear-energy-powered turbojet engine and optimum engine operating conditions and to determine gross weight and load-carrying capacity of airplane powered by such an engine. The size of airplane required to carry disposable load of 20,000 pounds was found to vary from approximately 300,000 to 900,000 pounds depending on assumptions. For a reactor tube-wall mean temperature of 2500 degrees R, turbine-inlet temperature of 2000 degrees R, reactor-free-flow-area ratio of 0.33, reactor-shielding-material specific gravity of 6.0, shielding thickness of 3.0 feet, and altitude of 30,000 feet, the airplane gross weight required to carry a 20,000 payload is 545,000 pounds" (p. 1).

Performance and boundary-layer data were taken in a 12 degree 10-inch inlet-diameter conical diffuser of 2:1 exit- to inlet-area ratio. These data were taken for two inlet-boundary-layer conditions. The first condition was that of a thinner inlet boundary later (boundary-layer displacement thickness, delta* approximately equal to 0.034) produced by an inlet section approximately 1 inlet diameter in length between the entrance bell and the diffuser. The second condition was a thicker inlet boundary layer (delta* approximately equal to 0.120) produced by an additional inlet section length of approximately 6 diameters. Longitudinal static-pressure distributions were measured fro wall static orifices. Transverse total- and static-pressure surveys were made at the inlet and exit stations. Boundary-layer velocity distributions were measured at seven stations between the inlet and exit. These data were obtained for a Reynolds number (based on inlet diameter) range of 1 x 10(exp 6) to 3.9 x 10(exp 6). The corresponding Mach number range was from M = 0.2 to choking. At the maximum-power-available condition supersonic flow was obtained as far as 4.5 inches downstream from the diffuser inlet with a maximum Mach number of M approximately equal to 1.5. The total-pressure loss through the diffuser in percentage of inlet dynamic …

From Introduction: "The primary purpose of the investigation described in the present described in the present report is to formulate a method which is of value for qualitative calculations of base pressure both on airfoils and bodies."

The state of polonium in aqueous solutions was investigated by means of ion exchange equilibrium studies. The distribution of the polonium between the solid and liquid phases was determined for solutions of various compositions using both a cation and an anion exchanges. These studies show that in the absence of a complexing agent polonium is hydrolyzed to such a degree that it forms monovalent cations and anions whose charge was not investigated in this study.

One of the problems connected with the sweptback wing is the difficulty of controlling the location of the center of pressure and hence the pitching moment. A method is presented for designing a wing to be self-trimming at a given set of flight conditions. Concurrently, the spanwise distribution of load on the wing is made to be approximately elliptical, in an effort to maintain low wing drag.

"An experimental investigation of the variation of aileron rolling effectiveness and total drag with Mach number has been made using 1/6-scale rocket-propelled models of the Bell MX-776. Three models having constant-chordwise-thickness full-span aileron at approximate deflections of 2 deg, 5 deg, and 15 deg have been flown. Positive control effectiveness over the Mach number range between approximately 0.5 and 1.2 was obtained from the models and no indication of reversal of effectiveness was encountered" (p. 1).

Report presenting wind-tunnel testing at Mach numbers of 1.5 and 2.0 to investigate the force, moment, and control characteristics of a canard missile configuration and its components in pitch and sideslip. The missile had small all-movable horizontal control surfaces at the nose and a cruciform wing at the rear, all of trapezoidal plan form. Trailing-edge flaps on the vertical fins were provided to supply directional control.

The following report analyzes several reported incidents of uranium-rich zirconium-uranium explosions. This report offers notes designed to describe conditions sufficient to cause an explosion with an 80% wt. uranium alloy.

Report presenting an investigation of an experimental 15-stage axial-flow compressor to determine the effect of inlet-annulus area blockage on disrupting the rotating stall and altering the overall performance and stall characteristics of the compressor. It is part of a general investigation to determine how to alleviate the general problems of blade vibration and poor off-design performance associated with compressor rotating stall.

Sea-level static testing of turbojet engine afterburner.

Report presenting a sea-level static investigation to determine the performance and some design principles for a short afterburner. The power section of a 12-stage axial-flow turbojet engine was used and the afterburner was designed to fit within the length required for the tail pipe used on the standard nonafterburning model.

Report presenting an investigation in the 8- by 6-foot supersonic wind tunnel to evaluate the performance of a translating-cone inlet operated over a range of Mach numbers and angles of attack. The effects of spike projection and internal flow area variation on pressure recovery, external drag, and corrected air-flow variation were determined.

A study of a series of three single-passage nozzles, designed to turn the flow at different velocity levels but to identical outlet conditions, in order to determine whether secondary-flow accumulations of boundary-layer fluids within nozzles could be minimized by use of low-velocity turning. Results indicated that the type of turning with subsequent acceleration is highly effective in minimizing secondary-flow accumulations at the corner where the suction surface joins the end walls.

From abstract: "A method for fabricating 30-in.-long stainless steel - uranium dioxide sheet was developed and the properties of the fabricated sheet were investigated."

Report presenting an investigation of the estimated minimum cooling requirements and related performance of turbojet engines equipped with high-performance single-stage turbines with air-cooled corrugated-insert blades over a range of turbine-inlet temperature, tip speed, and hub-tip radius ratio for Mach number 2 at 50,000 feet. The effects of stress-ratio factor, flight Mach number, altitude, turbine rotor impeller efficiency, and outside heat-transfer coefficient on cooling requirements were also investigated.

Report presenting an investigation to determine the effect on performance of two methods of throat-area modulation of two convergent plug nozzles. Data were obtained over a range of pressure ratios. Results regarding the performance of the translatable outer-shell-type plug nozzle, performance of the iris-outer-shell-type plug nozzles, sensitivity to throat-area variation, and air-flow parameter are provided.

This report describes the evaluation of physical properties of AGHT and 185-W graphites that are important to pile construction and operation. On the basis of these data, purified AGHT graphite was allocated to either filler block positions in the central regions of the K piles or to the upper or lower reflectors. This decision was based on the similarities of physical properties between AGHT graphite and the other moderator components. A similar allocation could be made for 185-W graphite for some future pile if it can be successfully purified or if purification is not required.

Free jet tests of 48 inch diameter ramjet combustor with annular can-type flame holder.

Report presenting an investigation in an NACA free-jet facility of a ramjet engine with an experimental 48-inch-diameter combustor. Three combustor lengths and three fuel-distribution systems were investigated over a range of fuel-air ratios and at two air flows. Results regarding the combustor performance and ignition data, velocity profile, and starting characteristics are provided.

"A ram-jet engine with an experimental 48-inch-diameter combustor was investigated in a free-jet facility. The combustor design comprised a large-volume annular pilot region and an array of sloping baffle- or gutter-type flameholders. The combustor was intended to operate at a fuel-air ratio of about 0.037" (p. 1).

Report presenting an investigation in a free-jet facility of a ramjet engine with an experimental 48-inch-diameter combustor. Three combustor lengths, three lengths of the shroud which separated the bypass air from the burning stream, and four fuel-distribution systems were investigated over a range of fuel-air ratios and a range of engine air flows. Results regarding the engine performance and ignition data, effect of fuel profile on combustion efficiency, total-pressure ratio, and distribution of static pressure in the main air stream are provided.

A large (size 2) Purex pulse generator was installed in the 321 Building Tan Farm to pulse solutions in the prototype Purex HA Column. Flow sheet considerations indicated a need for information on leakage rates with various size weep holes in the pulse generator piston. In addition to leakage tests, experiments were conducted to determine the air required under the piston to hold the column contents away from the pulse generator piston thereby preventing leakage during shut down and the determine the time required to bleed the air trapped in the pulse leg when the column is first filled. [...] Leakage past the piston was not appreciably affected by pulse frequency. [..] Bleeding the air out of the pulse leg under start-up conditions, even with the piston weep hole plugged, was rapid. The longest time required to bleed the pulse leg was 36 minutes, which included a column-filling time of 30 minutes.

Abstract: "The elastic double scattering of deuterons by complex nuclei has been investigated experimentally. Measurements were made on carbon, aluminum, and copper at around 157 Mev; on lithium, beryllium, and carbon at around 125 Mev; and on carbon and aluminum at 94 Mev. The expected tensor components of the deuteron polarization have not been observed. Measurements have been made of the differential cross section and vector-type polarization as a function of angle for the scattering of deuterons from the above elements, at the above energies. The observed polarizations were larger than would be expected on the basis of the individual nucleon-nucleus interactions. In a second experiment we measured the 169-Mev proton-proton polarization at 10, 15, 22.5, 30, and 35 in the laboratory system. The results indicate that partial waves up to and including L = 3 are important at this energy."

This report presents the best estimate possible on the basis of the available information as to how high an energy would be necessary in order that the gas pressure which could be tolerated would be attainable with present techniques (say 10-(-7) mm Hg.)