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 summarizing the results of geological exploration of the Atkinson Mesa area of Montrose County, Colorado and contains a brief description of the area's geology and ore deposits.

A report about how the U. S. Geological Survey explored the Atkinson Mesa area for uranium and vanadium bearing deposits from July 2, 1951, to June 18, 1953, with 397 diamond drill holes that totaled 261,251 feet.

A report regarding exploration for uranium deposits in the Atkinson Mesa area, Montrose County, Colorado. Concerns work done on behalf of the division of Raw Materials of the U.S. Atomic Energy Commission.

Report presenting flight measurements of the buffeting characteristics of the Bell X-5 airplane at 58.7 degrees of sweepback at a range of Mach numbers and altitudes. Information about tail buffeting and wing buffeting at several angles of attack is provided. The pilot considered the buffeting to be unobjectionable throughout the entire test region.

"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).

"An experimental investigation has been conducted to determine the dynamic stability and control characteristics in hovering and transition flight of a 0.13-scale flying model of the Convair XFY-1 vertically rising airplane with the lower vertical tail removed. The purpose of the tests was to obtain a general indication of the behavior of a vertically rising airplane of the same general type as the XFY-1 but without a lower vertical tail in order to simplify power-off belly landings in an emergency. The model was flown satisfactorily in hovering flight and in the transition from hovering to normal unstalled forward flight (angle of attack approximately 30deg)" (p. 1).

A guide to growing, harvesting, and selling peanuts. Includes descriptions of peanut varieties.

This is a progress report of the production reactors on the Hanford Reservation for the month of April 1954. This report takes each division (e.g., manufacturing, medical, accounting, occupational safety, security, reactor operations, etc.) of the site and summarizes its accomplishments and employee relations for that month.

This paper is issued in two volumes: LA-1664 and LA-1665. In LA-1664, the fundamental properties of a shock in free air are described, including the reasons for failure of similarity scaling. The results of an analytic solution for strong shocks are presented, which permit a determination of the energy in a shock wave from its rate of growth without recourse to similarity assumptions; from it the scaling laws for both homogeneous and inhomogeneous atmospheres are explicitly shown. The total energy is evaluated in a machine calculation for the blast wave and from this evaluation, the free air wave form for all hydrodynamic variables is presented. The general nature of the laws governing thermal radiation from atomic bombs is deduced, a new figure of merit for thermal radiation is suggested to replace the concepts of “thermal energy” and “critical calories,” which are considered ambiguous. Partition of energy is considered negligible in most cases of interest; the waste heat concept is reconsidered and the failures of scaling to TNT are regarded primarily as a failure of the ideal gas law. LA-1665 is concerned with preparation of height of burst curves. In the reflection process over ideal surfaces, the usual subdivision into regions …

This paper is issued in two volumes: LA-1664 and LA-1665. In LA-1664, the fundamental properties of a shock in free air are described, including the reasons for failure of similarity scaling. The results of an analytic solution for strong shocks are presented, which permit a determination of the energy in a shock wave from its rate of growth without recourse to similarity assumptions; from it the scaling laws for both homogeneous and inhomogeneous atmospheres are explicitly shown. The total energy is evaluated in a machine calculation for the blast wave and from this evaluation, the free air wave form for all hydrodynamic variables is presented. The general nature of the laws governing thermal radiation from atomic bombs is deduced, a new figure of merit for thermal radiation is suggested to replace the concepts of “thermal energy” and “critical calories,” which are considered ambiguous. Partition of energy is considered negligible in most cases of interest; the waste heat concept is reconsidered and the failures of scaling to TNT are regarded primarily as a failure of the ideal gas law. LA-1665 is concerned with preparation of height of burst curves. In the reflection process over ideal surfaces, the usual subdivision into regions …

Memorandum presenting a study of the ignition of ammonia and mixed oxides of nitrogen at 160 degrees Fahrenheit made with and without fuel additives utilizing small-scale rocket engines of approximately 200 pounds thrust. All experiments were conducted at sea-level pressures except two at a range of pressure altitudes. Results regarding the use of lithium as a catalyst, calcium as a catalyst, and no apparent catalyst are provided.

From Summary: "The presence of radomes and instruments that are sensitive to water films or ice formations in the nose section of all-weather aircraft and missiles necessitates a knowledge of the droplet impingement characteristics of bodies of revolution. Because it is possible to approximate many of these bodies with an ellipsoid of revolution, droplet trajectories about an ellipsoid of revolution with a fineness ratio of 10 were computed for incompressible axisymmetric air flow. From the computed droplet trajectories, the following impingement characteristics of the ellipsoid surface were obtained and are presented in terms of dimensionless parameters: (1) total rate of water impingement, (2) extent of droplet impingement zone, and (3) local rate of water impingement."

Report presenting an investigation to study the aerodynamic problems associated with a turbine design for a mode of engine operation which utilizes turbine stator adjustment to maintain a fixed compressor operating point. An indication of the turbine requirements for a particular compressor operating point indicated that a feasible sing-stage air-cooled turbine design could be obtained within reasonable aerodynamic limits. Results regarding the performance of the turbine, pressure ratios, and operational requirements are provided.

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.

The following report presents the results of various investigations on the study of the durability of concrete exposed to natural weathering. The report is divided into two parts: first, the natural weathering exposure stations and test procedures are analyzed, then follows the analysis of the programs of investigations.

Report describing a supersonic-compressor rotor designed as an impulse-type with some deceleration along the tip and with turning to the axial direction. Results regarding the overall performance, inlet flow distribution, results of rotor-outlet surveys, blade element performance at 90 percent design speed, and blade element performance at open throttle are provided.

Report presenting testing on 31 airfoils to determine the effects of thickness, trailing-edge bluntness, boattailing, and forward profile on the aerodynamic characteristics of thin airfoils, and to provide a check on available theoretical methods. The airfoils were 2, 4, and 6 percent thick and were tested at two Mach numbers at three Reynolds number in clean condition and one with transition fixed.

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The following quarterly report covers the period of January, February and March of 1954, discussing medical and health physics such as: the metabolic properties of various materials, biological studies of radiation effects, lipoprotein studies, health chemistry, and health physics.

Summary of miscellaneous updates related to the project. This includes information on the following. Simplified equations for modeling reactor conditions. Solubility tests involving thorium, bismuth, and protactinium. various other measurements and tests involving thorium, uranium, protactinium, bismuth, aluminum, and various other salts.

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.

Note presenting tables and figures of a standard atmosphere based on the Manual of the ICAO Standard Atmosphere. Detailed tables of pressures and densities are given for altitudes up to 20,000 meters and to 65,000 feet.

Report presenting an investigation to determine the blade torsional deflection of three supersonic-type propellers at various operating conditions. Blade-torsional deflection was found to produce appreciable results that can be predicted by theory with good accuracy. Results regarding the efficiency, thrust coefficient, and power coefficient are provided.