Report presenting an investigation to measure the effect of base bleed on the base pressure, lift, drag, and pitching moment of a 10-percent-thick blunt-base airfoil model. Small holes near the lower surface near the trailing edge into the base region were used to create base bleed. The drag was reduced as a result of the bleed holes.

Report presenting a flight investigation of four air-to-air missiles mounted by pylons on a rocket-powered basic wingless buffet-research vehicle to determine the trim, buffet, and drag characteristics of the combination.

Report presenting an investigation to determine the zero-lift rolling effectiveness of all-movable sweptback horizontal tail fins mounted behind a notched delta wing at a constant angle of differential incidence of 7 degree per fin. Two models, one with a stiff wing and one with a flexible wing, were tested in free flight over a range of Mach numbers. The rolling effectiveness was about the same magnitude at subsonic and supersonic speeds for both models.

This document presents a summary of work and progress at the Hanford Engineer Works for December 1954. The report is divided into sections by department. A plant wide general summary is included at the beginning of the report, after which the departmental summaries begin. The Manufacturing Department reports plant statistics, and summaries for the Metal Preparation, Reactor and Separation sections. The Engineering Department`s section summarizes work for the Technical, Design, and Project Sections. Costs for the various departments are presented in the Financial Department`s summary. The Medical, Radiological Sciences, Utilities and General Services, Employee and Public Relations, and Community Real Estate and Services departments have sections presenting their monthly statistics, work, progress, and summaries.

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"Small-perturbation spectral-analysis techniques are used to obtain the root-mean-square flame-generated turbulence velocities and the attenuating pressure fluctuations stemming from interaction of a constant-pressure flame front with a field of isotropic turbulence in the absence of turbulence decay processes. The anisotropic flame-generated turbulence velocities are found to be of about the same intensity as those of the incident isotropic turbulence, the lateral turbulence velocities being always lower, but the longitudinal velocity is somewhat increased for flame-temperature ratios over 7" (p. 599).

Memorandum presenting an investigation of the performances of two annular diffuser designs applicable to turbojet afterburner installations to determine the effectiveness of injection and suction boundary-layer controls. Results regarding inlet measurements, flow observations, static-pressure distributions, downstream velocity distributions, and mean performance coefficients are provided.

Report presenting limited flight measurements made in order to investigate the effect of dynamic vibration absorbers on the structural response of a Lockheed F-80A airplane during buffeting. The results were obtained by comparison of data with and without the absorbers operating through use of electrical frequency-analysis techniques.

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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; Constitutionality of House Bill No. 215 which establishes two subdivisions to Article 7428, V.C.S., and further defines a conspiracy in restraint of trade under that article.

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; Constitutionality of House Bill 256, 54th Legislature

From Introduction: "The purpose of this paper is to present an analysis of the data for the remaining airplanes where the data were sufficient to warrant analysis. The data analyzed represent totals of 351 to 5660 hours of operations with ten types of Navy airplanes and were recorded during the period 1949 to 1953."

Report presenting testing of a towed airplane model in the 19-foot pressure tunnel in conjunction with the development of a flutter testing technique. The model was equipped with an autopilot to keep the model flying straight and level in the tunnel while restrained only in drag. Results regarding period and cycles to damp to half amplitude, time histories, and motions of the flexible wing model are provided.

From introduction: "The objective of this report is to present the results and describe the tests of both the 2-in. D and 6-in. D contractors using mill pulp feeds. Work on determining resign attrition is also reported. ORNL-CF-52-12-101 described the results of preliminary tests using synthetic ore pulps."

Report presenting the results of a wind-tunnel investigation to determine the effects of various free-flight rocket-model booster-adapter configurations on the aerodynamic characteristics in pitch and sideslip of a swept-wing, fighter airplane model with a Mach number of 2.01. Results regarding the effect of adapter shape and aerodynamic characteristics of the model alone are provided.

Report presenting results of a wind-tunnel investigation to determine the effects of various free-flight rocket-model booster-adapter configurations on the aerodynamic characteristics in pitch and sideslip of a swept-wing, fighter airplane model for a Mach number of 2.01. Normal-force, lateral-force, pitching-moment, and yawing-moment coefficients of the airplane model were measured, and schileren photographs of the various configurations were obtained.

From Summary: "Measurements of pressure distributions have been made over a wing midsemispan station on the 35 degree sweptback wing of the Douglas D-558-II research airplane at Mach numbers from 1.17 to 2.0. The results of the investigation indicate that, as the angle of attack increased at the higher Mach numbers, the pressure coefficient for a vacuum limited the extent to which the upper-surface pressures could expand. Consequently most of the increase in section normal-force coefficient at high angles of attack can be attributed to the increase in pressure over the lower surface."

Preliminary results are presented from an investigation to determine the influence of afterbody geometry on the effects of a sonic propulsive jet at transonic speeds. The results presented are base pressure coefficient and afterbody pressure-drag coefficient as a function of jet pressure ratio for different values of Mach number and jet temperature. Geometric parameters investigated include boattail angle, jet-to-model diameter ratio, and jet-to-base diameter ratio.

Abstract: "The trajectory analysis of an immobilized plasma has been generalized to include the presence of electrons having a far similar radius of gyration and, therefore, fitting readily into the broader scale structure established by the ions. This problem has been adapted to machine calculations and the results for various strengths plasmas have been calculated."

Nickel-plated uranium corrosion samples, 1 inch dia. X 0.180 inch thick, press-clad with 30-mil aluminum at both 10 and 15 thousand psi, show improved corrosion resistance over samples press-clad at 6 thousand psi with the same time-temperature conditions. Design of equipment for the internal cladding of uranium tubes is progressing. The basic tools will be applicable to several variations of the proposed method of {open_quotes}inverse die sinking.{close_quotes} Analyses of double and triple melted Horizons` electrolytic thorium show a significant increase of H{sub 2} and O{sub 2}, upon remelting with a corresponding increase in the hardness of the metal.

From Introduction: "Numerous tests of tip controls on delta wings at transonic and low supersonic speeds have shown that such configurations provide satisfactory rolling-moment effectiveness, and that the hinge can be controlled by proper location of the hinge line (ref. 1). The purpose of the present tests is to determine the characteristics of such a configuration at Mach number of 4.04 and a Reynolds number of 5.8 X 10^6, based on the wing mean aerodynamic chord."

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