From introduction: "This report covers the development of nondestructive techniques for measuring quantitatively: (1) thickness of electrodeposited-nickel diffusion barriers, and (2) thickness of aluminum cladding on flat-plate fuel elements."

This report provides details of a test to determine the feasibility of preventing corrosion of the 107- C retention basins by the installation of a small scale cathodic protection system.

during the December 1953 extended outage the process water flow at C Reactor was increased and redistributed to allow reactor operation with a 69 tube enrichment ring in the third lattice unit and with the maximum protection afforded by the trip before boiling operational concept. The redistribution was accomplished by the installation of individual venturi flow meters on approximately 1800 process tubes. Flow and pressure requirements were met by the installation of larger diameter conventional Hanford orifices on about 200 tubes. During the outage, the original Panellit gages were replaced with improved Panellit gages equipped with long vane mercoid switches. The purpose of this memorandum is to review and report the results of the reorificing program and to compare them with predicted behavior.

During a routine beta-gamma hand and shoe count, an employee discovered that his shoes were contaminated. This document discusses the spread of particulate contamination at the Biophysics Laboratory, Building 329, 300 Area on July 6, 1954.

Letter opinion issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, John Ben Shepperd, regarding a legal question submitted for clarification; Refund of Texas erroneously paid Texas Citrus Commission.

Letter opinion issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, John Ben Shepperd, regarding a legal question submitted for clarification; Effect of omission of the name of a candidate for justice of the peace from the general election ballot.

Letter opinion issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, John Ben Shepperd, regarding a legal question submitted for clarification; Wheter Article 21.38, Insurance Code of 19.01, authorizes a licensed agent to procure insurance from an unauthorized company on the ground that the particular type of insurance was not written by an authorized company.

Letter opinion issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, John Ben Shepperd, regarding a legal question submitted for clarification; Transfer of monies of the Commodity Distribution Program to the separate revolving funds.

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Free flight tests of 45-deg swept wings of 3.15 aspect ratio and 0.54 taper ratio to measure wing damping and possible transonic flutter.

Report discussing an investigation to determine the effects of aeroelasticity on the rolling effectiveness of a model of a McDonnell F3H-1 airplane wing. The plane was found to be subject to aeroelastic losses that varied with Mach number and altitude.

Memorandum presenting an investigation in the 7- by 10-foot tunnel to determine the effect of wing-root leading-edge and scoop-type jet-engine air-inlet configurations on the static longitudinal stability characteristics and the duct-flow characteristics of a scale model of the MX-1764 airplane. The addition of the inlet configurations to the model generally resulted in slight reductions in longitudinal stability and increases of maximum lift coefficient.

Report presenting an investigation to determine the effects of six stabilizing fin plan forms and three body-nose configurations on the static stability of a 20 degree cone-cylinder body of revolution that had a fineness ratio of 8.65. The fin plan forms tested were swept untapered fins with 45 and 60 degrees sweep angles, trapezoidal fins, and delta fins. Results regarding the normal force coefficient, pitching moment coefficient, and center of pressure are provided.

Report presenting thrust-reversal performance of several basic target-type jet reflectors of various sizes and with various modifications obtained with unheated air over a range of exhaust-nozzle pressure ratios. Maximum, or near maximum, reversal for any deflector occurred at a spacing which was mechanically feasible and did not affect nozzle air flow.

Report presenting an investigation in the flutter research tunnel to determine the oscillating forces and moments on a two-dimensional wing equipped with an oscillating circular-arc spoiler. The study indicated that force and moment coefficients and their phase angles are affected by Reynolds number, Mach number, and reduced frequency.

From Introduction: "Reported herein are the over-all engine performance and the starting and windmilling characteristics. Data are presented in the form of performance maps at each flight condition to show the effects of altitude and flight Mach number on various engine-performance variables. The effect of engine deterioration with operating time on performance is also discussed."

From Summary: "A compilation has been made of available information on the problem of support interference at transonic and supersonic speeds. This compilation indicates that at supersonic speeds there are sufficient experimental data to design properly sting supports and shrouds having negligible interference. At transonic speeds the interference problem becomes more acute, and more experimental information is needed."

Report presenting an investigation to determine the effect of spanwise variations in thickness ratio on the aerodynamic characteristics of wings at transonic speeds. Lift, drag, and pitching-moment data rare presented for 3 wings with different taper ratios. Testing occurred over a range of Mach and Reynolds numbers.

From Summary: "An experimental investigation of a series of four convergent-divergent exhaust nozzles was conducted in the Lewis 8-by-6 foot supersonic wind tunnel at Mach numbers of 0.1, 0.6, 1.6, and 2.0 over a range of nozzle pressure ratios. The thrust characteristics of these nozzles were determined by a pressure-integration technique. From a thrust standpoint, a nozzle designed to give uniform parallel flow at the exit had no advantage over the simple geometric design with conical convergent and divergent sections."

Report presenting the aerodynamic design and design-point performance of a 16-inch impulse-type supersonic-compressor rotor component with turning to the axial direction, including an off-design and stage performance analysis. Results regarding rotor component performance, discussion of rotor performance, stage consideration for rotor performance, stage performance, and stator performance are provided.

Report presenting an investigation of wings of aspect ratios of 4, 3, and 2 with a plan-form taper ratio of 0.5 and a thickness taper ratio of 0.33 to determine their transonic longitudinal characteristics and effects of tapering thickness ratio. Results regarding the combined effects of aspect ratio and thickness ratio and effects of tapered thickness ratio are provided.

Report presenting an investigation to determine the static characteristics of a two-blade NACA 10-(3)(062)-045 propeller. Experimental data were obtained for a blade-angle range from -5 degrees to 40 degrees measured at the 0.75 radial station and for tip Mach numbers up to 1.0.

Report presenting an investigation to determine the effect of several chord-extension configurations at low speed on a variable-sweep airplane model with a partially cambered wing. Testing occurred at a designated Reynolds number based on the mean aerodynamic chord of the wing at 50 degrees sweep for average test conditions. Results regarding the effect of chord extensions at 50 degrees, 60 degrees, and 20 degrees sweep, effect of chord extensions on lateral stability, and a comparison with different wing modifications are provided.

Report presenting an investigation of the section and panel characteristics and loads obtained from pressure measurements over a 35 degree sweptback wing at level-flight lifts for a range of Mach numbers. Section pressure distributions were taken at the root, midspan, and tip stations of a Douglas D-558-II airplane.