Memorandum presenting an altitude investigation to determine the basic mechanism by which J65-W-4 turbine rotor-blade failures were occurring in service. The engine was installed in an altitude test chamber and a series of controlled engine throttle bursts, with and without inlet-air distortion, over a range of altitudes, flight Mach numbers, and inlet-air temperatures. An examination of the data obtained during the investigation indicated that the danger of turbine failure could be eliminated without any appreciable sacrifice in engine acceleration time.

"A program to investigate the aerodynamic heat transfer of a nonisothermal hemisphere-cylinder has been conducted in the Langley 11-inch hypersonic tunnel at a Mach number of 6.8 and a Reynolds number from approximately 0.14 x 10(6) to 1.06 x 10(6) based on diameter and free-stream conditions. The experimental heat-transfer coefficients were slightly less over the whole body than those predicted by the theory of Stine and Wanlass (NACA technical note 3344) for an isothermal surface. For stations within 45 degrees of the stagnation point the heat-transfer coefficients could be correlated by a single relation between local Stanton number and local Reynolds number" (p. 1001).

Report presenting a continuous sampling-probe technique used to determine the percentage of JP-5 fuel spray evaporated under conditions common in ramjet engines. Fuel was injected contraststream from a multiple-orifice injector and sampling data were obtained at several distances downstream of the injector. An expression is generated for a description of this phenomenon.

Memorandum presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effects of various vertical locations of the wing and horizontal tail on the aerodynamic characteristics in pitch and of a supersonic airplane configuration at Mach number 2.01. The model was equipped with a wing and horizontal tail, each having a 45 degree sweep and an aspect ratio of 4. The configurations investigated included a high-wing, a mid-wing, and a low-wing arrangement, each with four different horizontal tail locations varying from a position 0.208 semispan below to 0.556 semispan above the body center line.

Report presenting testing of a rocket-propelled model of an airplane with an arrow wing with a 55 degree leading-edge sweep and a flat-sided fuselage mounting swept horizontal and vertical tails using the pulsed-control technique at a range of Mach numbers. Results regarding longitudinal trim, lift and stability, drag, lateral force, and thrust and jet effects are provided.

"The oscillating air forces on a two-dimensional wing oscillating in pitch about the midchord have been measured at various mean angles of attack and at Mach numbers of 0.35 and 0.7. The magnitudes of normal-force and pitching-moment coefficients were much higher at high angles of attack than at low angles of attack for some conditions. Large regions of negative damping in pitch were found, and it was shown that the effect of increasing the Mach number 0.35 to 0.7 was to decrease the initial angle of attack at which negative damping occurred" (p. 521).

The radiators designated Cambridge #1 and #2 were visually examined and modified before operation. The initial examination revealed poor quality braze joints at the top and bottom plates of Cambridge #1. However, the same plates of Cambridge #2 were adequately brazed. The copper core of the fins was exposed in many of the tube-to-fin joints on both radiators, indicating that the braze material had not covered the fin collars. Samples were removed from each radiator and examined for evidence of mass transfer. Samples were also removed from the air inlet and outlet banks of both radiators and examined for fin-to-tube integrity.

Introduction: This memo gives a general description of the components and equipment affecting the control of the SRE, and the equipment associated with all reactor services.

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The enthalpy and heat capacity of Composition No. 30 (NaF-- ZrF/sub 4/-- UF/sub 4/; 50--46--4 mole%) were determined with and without the addition of fluoride salts (RbF, BaF/sub 2/, LaF/sub 3/) simulating fission products. (L.T.W.)

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From abstract: "The purpose of this note is to consider the feasibility of conducting kiloton-weapons tests in underground holes sufficiently deep so that the explosion will be effectively contained. Such a shot would have the advantage that it could be detonated independently of weather conditions, and thus would allow greater freedom in the test program."

This is the monthly report for the Hanford Laboratories Operation. Metallurgy, reactor fuels, physics and instrumentation, reactor technology, chemistry, separation processes, biology, financial activities, employee relations, laboratories auxiliaries, radiation protection, operations research, inventions, visits, and personnel status are discussed. This report is for November, 1956.

This document presents a summary of work and progress at the Hanford Engineer Works for April 1956. 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 summaries 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 Service departments have sections presenting their monthly statistics, work, progress, and summaries.

This is the monthly report for the Hanford Laboratories Operation, February, 1956. Metallurgy, reactors fuels, chemistry, dosimetry, separation processes, reactor technology financial activities, visits, biology operation, physics and instrumentation research, employee relations are discussed.