"Results are reported of current studies at the Forest Products Laboratory to develop a metal-bonding adhesive with greater resistance to temperatures up to 600 degrees Fahrenheit that is easier to use than present ones. Most promising is a formulation of phenol and epoxy resins modified with hexamethylenetetramine and supplied for use as a dry tape supported on a glass-mat base" (p. 1).

Drag and longitudinal trim at low lift of the North American YF-100A airplane at Mach numbers from 0.76 to 1.77 as determined from the flight test of a 0.11-scale rocket model are presented herein. Also included are some longitudinal stability and some qualitative pitch-damping data.

Report documenting the suitability of Kansas for plant locations to produce synthetic liquid fuels, based on raw materials, water sources, and local interest.

Memorandum presenting a summary of heat-resistant materials obtained from interviews with alloy producers, jet-engine manufacturers, and research laboratories in Britain during October and November 1950. The primary subjects of interest included the properties of materials and service requirements for gas turbines, criteria used for judging and inspecting materials, and research developments of both a practical and fundamental nature in the field.

An analysis of the longitudinal characteristics of swept wings which is based on available large-scale low-speed data and supplemented with low-scale data when feasible is presented. The emphasis has been placed on the differentiation of the characteristics by a differentiation between the basic flow phenomenon involved. Insofar as possible all large-scale data available as of August 15, 1951 have been summarized in tabular form for ready reference.

This report is the first volume of a two-part set documenting the results of the analyses of the airborne gamma radiation and total magnetic field survey that was flown for the Dillon National Topographic Map NL12-7.

Average record data listings taken during aerial gamma-ray and magnetic surveys of the Dillon Quadrangle in Montana and Idaho.

Single record data listings taken during aerial gamma-ray and magnetic surveys of the Dillon Quadrangle in Montana and Idaho.

Report presenting an investigation at high subsonic speeds of a complete model with one of four types of wings: a basic sweptback wing, an M-shaped wing, a W-shaped wing, and a cranked wing. All of the wings had the same aspect and taper ratio and were tested at the same range of Mach numbers. Results regarding longitudinal characteristics and lateral characteristics of the different wings are provided.

From Summary: "Heating requirements for satisfactory cyclic de-icing over a wide range of icing and operating conditions have been determined for a gas-heated, 36 degree swept airfoil of 6.9-foot chord with a partial-span leading-edge slat. Comparisons of heating requirements and effectiveness were made between the slatted and unslatted portions of the airfoil. Studies were also made comparing cyclic de-icing with continuous anti-icing, and cyclic de-icing systems with and without leading-edge ice-free parting strips. De-icing heat requirements were approximately the same with either heated or unheated parting strips because of the aerodynamic effects of the 36 degrees sweep angle and the spanwise saw-tooth profile of leading-edge glaze-ice deposits. Cyclic de-icing heat-source requirements were found to be one-fourth or less of the heat requirements for complete anti-icing. The primary factors that affected the performance of the cyclic de-icing heating system were ambient air temperature, heat distribution, and thermal lag."

From summary: Graphs of various gamma radiation spectra, taken by plotting data from a single channel pulse height analyzer, are compared with photographs of gamma radiation spectra presented on the tube face of the Hughes Memoscope Model 104.

Report presenting an experimental investigation at zero flight speed and sea-level conditions on a 4000-pound-thrust centrifugal-flow-type turbojet engine to determine the amount of thrust augmentation obtainable at maximum rotor speed by the injection of water, alcohol, and water-alcohol mixtures at the compressor inlets. A maximum thrust augmentation of 26 percent was obtained by the injection of 4.5 pounds per second of water and 2.0 pounds per second of alcohol. Results regarding the tail-pipe gas temperature, air-flow and compressor-outlet pressure, fuel flow, specific liquid consumption, and thrust augmentation are provided.

The system Dovex 21K and aqueous uranyl sulfate solutions were studied in the solution compositions range: 0-0.005 mol/liter uranyl sulfate, 0.15 mil/liter total sulfate, 0.02 mol/liter H2SO4 (pH 2).It is shown that UO3SO4 and/or UO2(SO4)2-/2 are sorbed on the resin to form R2UO2(SO4)2. It is surmized that these same species are also involved at high uranyl concentrations and pH 2 it is suggested that U2O5SO4, U2O5(SO4)2-/2, and R2U2O3SO4 species may be involved.

"A 1/10-scale rocket model of the Lockheed XF-104 with faired inlets has been flown over a Mach number range from 0.80 to 1.45 to determine low-lift drag and a limited amount of stability data. The center-of-gravity locations were 4.0 and 1.5 percent of the mean aerodynamic chord before and after sustainer firing, respectively. Oscillations induced by pulse rockets were used to determine stability data. The external transonic drag coefficient increased from a value of 0.0160 at Mach number 0.80 to a maximum of 0.0432 near Mach number 1-13, with a drag rise Mach number of about 0.93. At Mach numbers where it could be determined, the model exhibited stable dynamic and static stability characteristics at low lift" (p. 1).

Report presenting testing of a series of single and double unswept, lateral-support struts at a Mach number of 1.9 on a cone-cylinder body at zero angle of attack. The struts consisted of a rectangular box section with identical wedge fairings fore and aft. Results regarding the shock-wave intersections and pressure distributions are provided.

From Summary: "An analysis of the flight time history of a rocket-propelled model of a 60 degree delta-wing airplane configuration, fired for the purpose of obtaining zero-lift drag data, indicated wing flutter and subsequent failure at low-supersonic Mach numbers. This flutter occurred during the unpowered decelerating portion of the flight. The behavior of the model during flight is discussed and the mass and stiffness characteristics of a duplicate wing are presented."

From abstract: "A simple electronic circuit is described, the use of which greatly improves the temperature regulations obtainable with Beta equipment. The circuit utilizes the time derivative of the temperature to counteract oscillation and overshoot. No other changes are required in existing equipment for installation of the stabilizer."

This report describes corrosion rate of uranium in hydrogen-saturated water appears to be constant with respect to time after a brief induction period and to involve only one type of over-all reaction, in which pitting effects are slight or nonexistent.

Over the past 13 years a considerable body of data on explosive cratering has been developed for application to nuclear excavation projects. These data were obtained from some ten cratering programs using chemical explosives (TNT or nitromethane) and seven nuclear cratering detonations. The types of media studied have ranged from marine muck to hard, dry basalt, although most effort has been devoted to craters in NTS desert alluvium and basalt. Considerable effort has also been devoted to the study with chemical explosives of the use of linear explosives and rows of point charges. This paper is intended to be a summary of these data and a statement of the understanding which has been developed from them.

Report discussing the effects of xenon-135 and samarium-149 on the reactivity of nuclear reactors. The findings are presented in a "general manner, so as to be applicable to both the Converter and PuP Reactors."

It was shown that without further major development the detectors proposed for the Body Monitor can be expected to detect 0.02 microcurie of plutonium at the center of the chest cavity. This is the permissible body burden of insoluble forms of plutonium. The detection level can be decreased by decreasing the background counting rate. Decreases in the background can reasonably be expected; it should be possible to detect a small fraction of the permissible body burden. If it can be shown, as suggested by other work, that americium will remain with plutonium, then within at least a few months after entry into the body it should be possible to measure the plutonium by detection of rays from Am²⁴¹.

Technical report of an investigation to determine a suitable material for sintering and casting of braze rings. Braze rings afford an excellent means of preplacing braze alloy on tube to head joints of radiators, heat exchangers, and similar applications. A cast ring is especially desirable because of its increased strength. Previous efforts at casting had used welding grade carbon blocks with the desired ring cavities machined into their surface. Conclusion: Stackpole grade 331 electro-graphite provided the best results of the materials investigation. It is hard and more readily machinable with conventional tools than other grades. Carbon, in general, proved to be more satisfactory especially due its ease and speed of fabrication.

Abstract: An alpha survey radiac employing a photomultiplier tube and scintillation detector has been developed. The instrument utilizes transistor circuitry and operates from two standard flashlight batteries. Four linear ranges are provided with full scale indication on the highest range corresponding to 10,000 g /m2 Pu2 39. The instrument was designed with .a separable probe and a telescoping extension for easier ground monitoring. A thorium metal source is attached to the instrument housing for checking instrument calibration in the field. The device conforms satisfactorily to the military requirements for altitude, humidity, vibration, shock, and storage. The operational battery life is in excess of 40 hours. Instrument error at low temperatures slightly exceeds the 20% accuracy requirement; however, adequate measurements are readily made by using the thorium check source to provide a check point. Instrument response to low energy X-rays is excessive. However, tests indicate that a simple lead filter will eliminate this difficulty.

Report presenting gas-to-blade heat-transfer coefficients and turbine heat-rejection rates obtained for a wide range of one-spool turbojet engine designs believed to be representative of engines that will employ turbine cooling. The values of heat-transfer coefficient and heat-rejection rates are applicable to both liquid- and air-cooled turbines. Results regarding the heat-transfer coefficients and heat-rejection rates for turbojet engine designs, total heat-rejection rates for various turbojet engine and flight conditions, and heat-transfer coefficients and heat-rejection rates for turboprop engine design are provided.