Memorandum presenting flight tests conducted with an F-86D airplane equipped with a director-type radar fire-control system with scope presentation of the attack display. The effects of two attack-computer parameters and one attack-display parameter on the tracking performance in the manual mode of operation were investigated. Results regarding fixed-sight tracking and tracking with scope presentation are provided.

Report presenting performance of a two-dimensional external-compression inlet designed for various methods of inlet-engine matching up to Mach 3 at Mach 1.89 and Mach 0. Results regarding shock geometry, two-shock ramps, isentropic ramps, profiles, and cowl drag for the various Mach number tests are provided.

Report presenting a longitudinal stability and control investigation of a model of the Convair B-58 external store over a range of Mach numbers. Normal force, chord force, and static and dynamic stability derivatives are provided. Abrupt pitching disturbances were created by step-function movements of the canard surface.

"This bibliography is a list of references pertaining to factors affecting the motion of the artificial earth satellite. References are foreign and domestic literature."

Preliminary geologic map of the Elk Ridge 3 NE quadrangle, San Juan County, Utah

Report issued by the Oak Ridge National Laboratory discussing work completed by the Applied Nuclear Physics Division during 1956. Summaries of experiments conducted and project developments are presented. This report includes tables, illustrations, and photographs.

Report discussing the use of hot-wire anemometers to measure circumferential traces of specific-mass-flow variation for various radial positions at the rotor exit. Results regarding the rotor blade-wake traces, relative total-pressure ratio, and centrifuging of low-momentum fluid are provided.

Report presenting preliminary tests of a counterrotating axial-flow supersonic compressor, which indicates that a flow limitation in the second rotor restricted the flow rate at design speed. The second-stage rotor was modified by increasing the flow area to increase the flow rate and improve flow stability. Results regarding the overall performance of the modified compressor, radial variation of flow conditions and performance parameters in the second rotor, stability of the shock wave in the second rotor, and individual stage performance are provided.

Report presenting flight testis using an F-86D airplane equipped with a director-type radar fire-control system with scope presentation of the attack display. The effects of two attack-computer parameters and one attack-display parameter on the tracing performance in manual mode were investigated.

Report discussing the aerodynamic loading characteristics of a 45 degree sweptback wing with leading-edge chord extensions, including the effects of a spoiler-slot-deflector aileron. The wing section loading, wing-panel loading, and chord-extension loading are described.

Memorandum presenting two rocket-propelled models flight tested at Mach numbers from 0.8 to 1.5 to determine the effect of a fuselage indentation on the drag of a 52.5 degree sweptback-wing-body configuration with two large strut-mounted store symmetrically located above and below the fuselage. The fuselage had a symmetrical, Mach number 1.0 indentation designed to cancel the wing area normal to the plane of symmetry. Results regarding total drag and pressure drag are provided.

Report presenting an analysis of the injection of water into the jet-engine exhaust in order to suppress noise during static ground operation of jet engines. The investigation is conducted with a simple rig which pumps high-pressure water into the exhaust of an afterburning jet engine. Results regarding the overall sound-pressure levels and frequency spectra of the noise are provided.

"Theoretical rocket performance for frozen composition during expansion was calculated for liquid methane with several fluorine-oxygen mixtures for a range of pressure ratios and oxidant-fuel ratios. The parameters included are specific impulse, combustion-chamber temperature, nozzle-exit temperature molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, isentropic exponent, viscosity, and thermal conductivity. The maximum calculated value of specific impulse for a chamber pressure of 600 pounds per square inch absolute (40.827atm) and an exit pressure of 1 atmosphere is 315.3 for 79.67 percent fluorine in the oxidant" (p. 1).

Report presenting the development of a method based on blade-element concepts to evaluate the effect of stall or choke-free angle-of-attack range on the attainable pressure rise and relative Mach numbers for cascades or single blade rows. The method was extended to evaluate the effect of usable compressor-stage flow range on the design parameters of the stage flow per unit area, pressure ratio, and rotative speed.

Report presenting the performance of a two-dimensional external-compression inlet designed for various methods of inlet-engine matching up to Mach 3 at Mach 1.89 and Mach 0.

Memorandum presenting a longitudinal stability and control investigation made over a range of Mach numbers of a scale model of the Convair B-58 external store. Normal force, chord force, and static and dynamic stability derivatives formed an important part of the results. Results regarding the hinge moments and longitudinal trim and force coefficients are also provided.

Report presenting the results of a limited research program initiated to study the effects of a hot propulsive jet on the longitudinal stability characteristics of a fighter-type airplane configuration. The data was obtained from a rocket-boosted free-flight model investigation over a range of Mach numbers using four models that differed only in the position and size of the horizontal tail. Results regarding the time histories, trim, normal force, pitching moment, aerodynamic-center location, dynamic stability, trim drag, and pressure data are provided.

Report presenting a boundary-layer-control investigation to determine the longitudinal aerodynamic characteristics and chordwise load distribution on a thin, untapered, semispan wing with an aspect ratio of 3.33 and NACA 65A004 airfoil sections. The results are presented without discussion.

Memorandum presenting an investigation of the effect of a 60 degree sweptback horizontal tail at two vertical locations on the static longitudinal stability of two 60 degree sweptback wing-body configurations with aspect ratios of 2.67 and 4.00 in the 8-foot transonic pressure tunnel. Tests were made at Mach numbers from 0.80 to 1.18 for angles of attack from -3 degrees to about 15 degrees.

Discussing evidence of the potential of uranium in The Republic of India

This report is submitted to the U. S. Atomic Energy Commission as a final summary safeguards and hazards evaluation of a proposed test reactor at its Vallecitos Atomic Laboratory in Alameda County of California. It is the purpose of this report to provide sufficient data to obtain an AEC facility license for the reactor.