Memorandum presenting testing of a D-558-II airplane with the wing slats fully extended, with and without inboard wing fences, and with the wing slats half extended and wing fences removed. In order to improve the stick-force characteristics at moderate and large angles of attack, additional tests were conducted with two bungees of differing stiffness alternately attached to the control column.

Report discussing testing of a helicopter rotor powered by pulse-jet engines located at the rotor-blade tips. The basic hovering characteristics of the rotor and propulsive characteristics of the pulse-jet engine were obtained at a range of engine speeds with the engines rigidly fixed to the blade tips and with the engines free to pivot. Measurements were also taken to determine the effect of inlet blockage on the power-off drag of the jet engines and the noise intensity in the vicinity of operating engines.

Introduction: "This report covers the contributions of UCRL to MTA research and development program during the period June 1 to November 30, 1953. In this program UCRL continues to work in close collaboration with the California Research and Development Company (CRD)."

"Increasing demands for higher afterburner performance have required operation at progressively higher fuel-air ratios, which has increased the occurrence and intensity of screeching combustion. The onset of screech may be followed by rapid destruction of the combustor shell and other combustor parts. Because of its destructive characteristics, considerable effort has been expended to understand and eliminate screech. NACA work on the screeching combustion problem prior to 1954 is summarized herein" (p. 1195).

Memorandum presenting the effect of magnesium particles of various equivalent diameters on the apparent viscosity, sedimentation ratio, and redispresibility of petroleum-stabilized magnesium-JP-4 slurries. Powders of the following equivalent diameters were investigated: 2.8, 3.8, 7.2, 9.3, 12.0, and 14.8 microns. An analysis of the experimental error and reproducibility of values of apparent viscosity, sedimentation ratio, and redispersibility of the slurries was also made.

An investigation by the transonic-bump technique of the static longitudinal aerodynamic characteristics of a series of thin, low-aspect-ratio, highly tapered wings has been made in the Langley high-speed 7- by 10-foot tunnel. The Mach number range extended from about 0.60 to 1.18, with corresponding Reynolds numbers ranging from about 0.75 x 10(6) to 0.95 x 10(6). The angle of attack range was from -10 degrees to approximately 32 degrees.

Report presenting testing of a circular scoop inlet located far forward on a parabolic body of revolution at a range of Mach and Reynolds numbers and mass-flow ratios. The inlet had an area equal to 8 percent of the body frontal area. Results regarding total and base drag coefficients, external drag coefficients, and inlet total-pressure recovery are provided.

The process of age calculation for Hanford exponential lattices containing aluminum-matrix slugs, where the sums run over the materials of the lattice cell.

A report discussing the determination of the size or areal extent of orebodies disclosed by drilling and by exploration underground.

"An investigation was made of the take-off characteristics of a 1/10-scale dynamic model of the Convair XF2Y-1 airplane. This airplane is a water-based, jet-propelled, delta-wing fighter incorporating a hydro-ski landing gear. Tests were made with the original configuration, with the beaching wheels removed, and with the wheels installed and fairings added in front of the wheels" (p. 1).

Memorandum presenting a five-stage axial-flow compressor with all rotor rows operating with transonic relative inlet Mach numbers designed as a research unit to study the potentialities and problems arising from the compounding of transonic stages. The report presents all design values and procedures, blade-row velocity diagrams, and the selection of blade shapes.

Memorandum presenting an evaluation of the overall performance of a 20-inch-diameter five-stage compressor as the initial step in an investigation of the potential performance and problems associated with a high-stage-pressure ratio compressor. The overall performance was evaluated over a range of flows at equivalent tip speeds from 40 to 100 percent of design. Results regarding the overall performance, compressor-inlet conditions, compressor-discharge conditions, stagewise variation of static pressure, and performance evaluation are provided.

Report presenting an investigation of the pumping characteristics of eight conical ejectors mounted on a fuselage portion of a supersonic airplane. The diameter ratio, spacing ratio, nozzle pressure, and ejector weight flows were varied. Results regarding the ejector pumping characteristics, comparison with previous results, comparison of data for cold and hot primary flow, and ejector air-supply requirements are provided.

Report presenting an investigation of the pumping characteristics of eight conical ejectors mounted on a scale fuselage portion of a supersonic airplane. The configurations simulated various positions of a two-position nozzle with a fixed shroud and double-iris exit. Results regarding ejector pumping characteristics, comparison with previous results, comparison of data for cold and hot primary flow, and ejector air-supply requirements are provided.

Report presenting an investigation to determine the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane with a 40 degree swept wing with an aspect ratio of 10. Results regarding components of the lift changes due to operating propellers, components of the pitching-moment changes due to operating propellers, effect of configuration changes on the pitching-moment characteristics of the model, stick-fixed longitudinal stability of the model, reduction of adverse effects of propellers on longitudinal stability, and propulsive characteristics are provided.

Report presenting an investigation to determine the aerodynamic characteristics of the NACA 4-(5)(05)-037 six- and eight-blade, dual-rotation propellers operating at positive and negative thrust at a range of Mach numbers when operating at near static conditions. The propellers were operated in combination with a long spinner and at a variety of blade angles.

This report follows an investigation with the purpose of studying the operational characteristics of a catalytic tube recombiner where the gases are passed over stainless steel tubes coated with platinum black.

"The transonic longitudinal aerodynamic characteristics of a 0.0858-scale model of the Lockheed XF-104 airplane have been obtained from tests at the Langley 16-foot transonic tunnel. The results of the investigation provide some general information applicable to the transonic properties of thin, low-aspect-ratio, unswept wing configurations utilizing a high horizontal tail . The model employs a horizontal tail mounted at the top of the vertical tail and a wing with an aspect ratio of 2.5, a taper ratio of 0.385, and 3.4-percent-thick airfoil sections" (p. 1).

"Free-flight tests in the transonic and supersonic speed ranges utilizing rocket-propelled models have been made on two pairs of 1/9-scale Convair YF-102 airplane wings with elevons to investigate the possibility of flutter . These wings had modified 60 deg delta plan forms with the trailing edge swept forward 5 deg. The aspect ratio of two exposed wing panels was 2.19 and the wings had NACA 0004-65 (modified) airfoil sections. The model wings and elevons were dynamic-scale models at sea level of the full-scale wings at 20,000 feet" (p. 1).