Abstract: "Approximate melting points have been determined for five samples of uranium tetrafluoride representing incompletely converted uranium dioxide and covering the range from about 2 to 20 w/o UO2, using the method of differential thermal analysis. The results indicate the melting temperatures are in the range of 920 to 980 C. No significant correlation between melting point and UO2 content was observed, possibly because of calcite formation. Similar results were obtained on synthetic mistakes of UF4 containing from 10 to 40 w/o UO2."

At about 6:30 a.m. one of the two Process Operators regularly stationed at 233-S was performing routine work in the Control Room, heard a nearby Poppy alpha detector breaking down.'' He checked and found the instrument appeared to be in operating condition as it would respond to a high level source. Further checking indicated that he was contaminated and that nearby horizontal surfaces were contaminated. This information was phoned to the Shift Supervisor who told the Operator that he would be right out and to throw a pair of shoe covers out the door. On arriving, the Supervisor donned the shoe covers and then quickly checked the Poppy response and confirmed the report of the Operator. Both men then left the building. Just outside they met the other Process Operator assigned to 233-S, returning from the lunchroom. The second Operator was handed a smear, previously taken and checked by the Supervisor, and told to check it on a Poppy in the load-out-room, a room adjacent to where the contamination was originally found. When the Supervisor heard the load-out-room Poppy break down as the smear was checked he instructed both Operators to stand by just outside the building while he went …

Memorandum presenting an annotated bibliography of NACA reports containing information of interest to designers and manufacturers of controls for turbojet engines. The eleven major topics include starting, acceleration, flame-out, temperature control, stability and dynamics of small disturbances, combustion dynamics, engine inlet diffuser control, steady-state engine performance, fuel systems, sensors, and general control system theory.

Memorandum presenting an investigation of a full-scale afterburner with high burner-inlet velocity conducted to determine burner performance with several variations in burner design. Variables receiving particular attention were flameholder design and burner length. Results regarding diffuser performance, performance of the reference two-V-gutter flameholder, designs to improve combustion for high-velocity conditions, and operational characteristics are provided.

Attenuation of tangent-pressure oscillation in liquid-oxygen-heptane rocket engine combustion chamber using longitudinal fin. Results regarding the engine performance with injector A, effect of fins with injector A, and destructiveness of screaming are provided.

Report presenting an acceleration control that operates on fuel flow and uses directly measured acceleration as the control signal as applied to an axial-flow turbojet engine. A study to determine the feasibility and dynamic characteristics of the control was undertaken. Results regarding the open-loop characteristics and closed-loop characteristics are provided.

The package boiler was operated at a maximum steam rate of 1750 Ib/hr at 1500 psi. The operation of the pumps, relief valves, gages, and pressure controller was checked. The time required for the boiler to come up to full operation was 15 to 20 min. On the basis of the test the boiler is considered to meet the manufacturer's specifications. (auth)

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Report presenting the stability characteristics of an axisymmetric conical inlet with supercritical spillage. Either injection or suction through the slot increased the stable subcritical range over that of the unmodified cone as much as 22 percent of the free-stream mass flow. Results regarding the effect of spike tip translation on inlet performance, effect of air injection and suction, secondary-flow requirements, comparison of various stabilizing methods, and effect of stabilizing devices on flow distortion are provided.

Report presenting an investigation of a full-scale afterburner with high burner-inlet velocity to determine burner performance with several variations in burner design. A total of 12 flameholder configurations were investigated at a specified burner-inlet velocity and a range of burner-inlet pressures. Results indicated that a basic annular two-V-gutter flameholder can operate at 90 to 95 percent combustion efficiency for fairly optimum burner length and pressure.

An investigation of the use of fins to prevent high-frequency combustion-pressure oscillations (screaming) in the combustion chamber of a 1000-pound-thrust rocket engine with a chamber pressure of 300 pounds per square inch and using liquid oxygen and n-heptane as propellants. Tangential combustion-pressure oscillations were found to be eliminated with longitudinal fins located in the combustion zone. Results regarding engine performance, effect of fins, and destructiveness of screaming are provided.