Memorandum presenting an analysis of the effect of adding fluorine to the Vanguard first-stage oxidant. An increase in specific impulse of 5.74 percent may be obtained with 30 percent fluorine. Charts are provided regarding the vehicle performance increases for a zero-drag vertical trajectory.

From Introduction: "This report presents data pertinent to the problem of boosting rocket performance by adding up to 30 percent liquid fluorine to the liquid oxygen of an existing oxygen-hydrocarbon rocket engine."

Increasing the volume and length of the duct behind the inlet affected the inlet stability at Mach 2.0 and zero angle of attack. Close approximation of the inlet stability limit of the J34 engine-inlet configuration was obtained by a cold-pipe configuration having a length and volume approaching that measured to the engine turbine. Variation of these parameters had a small effect on the minimum subcritical stable mass flow below a cowl-lip-position parameter of 44 degrees and appeared to have a negligible effect on the inlet pressure-recovery - mass-flow curve. Initial buzz frequency and minimum cowl-lip-position parameter for complete buzz-free operation varied with configuration.

The General Electric Company is designing and building a 180,000 kilowatt nuclear power plant for the Commonwealth Edison Company at a site near the confluence of the Kankakee and Des Plaines Rivers in Grundy County, Illinois, about 47 miles southwest of Chicago. The plant will be known as the Dresden Nuclear Power Station, and will employ a nuclear reactor of the dual-cycle boiling water type.

An estimate has been made of the gamma radiation levels at access holes in the HRT Shielding when the plugs have been removed to service or maintain the reactor. In every case the radiation level at the holes was greater than the maximum permissible exposure rate of 0.3 roentgens per week. The radiation through the holes can be attenuated to some extent by flooding the reactor cell up to the flange to be disconnected. However, shielding would still be required and it is more practical to provide a small additional shield thickness to compensate for the moderate attenuation that could be gained from flooding.

At a corrected speed of 1100 feet per second, the low-blade-angle rotor operated with a relative inlet Mach number of 1.2, a diffusion factor of 0.65, and an axial velocity ratio of 0.71 in the tip region (11 percent of passage height away from the outer wall). The measured minimum-loss coefficient was 0.35, and this value falls above a previous correlation of rotor losses with diffusion factor. Through a comparison with data for three other rotors, the occurrence of high losses was related to a high suction-surface Mach number. These comparisons also indicated that axial velocity ratios between 0.73 and 1.10 have no independent effect on losses.

This report is the result of a study to develop heat-resistant fin materials possessing a high thermal conductivity for air radiators. Since an economical and commercially feasible product was desired, the investigation was restricted primarily to a study of electroplated copper, clad copper, and copper alloys. Sheet material 0.008 to 0.010 in. thick was evaluated for fabricability and for metallurgical stability and thermal conductivity at 1500°F. From the results of the rests it was concluded that: (1) electroplates were unsatisfactory; (2) clad-copper fins possessing a thermal conductivity of 50% of that of copper are commercially feasible; (3) copper-aluminum alloys possessing a thermal conductivity approaching that of copper at 1500°F are possible. Service tests of clad copper and the copper-aluminum alloys indicate that the choice of materials will be dictated by the requirements of the radiator, since each presents some unique problems.

Memorandum presenting an investigation with a ramjet utilizing pentaborane fuel in order to evaluate promising high-energy fuels under actual flight conditions. During descent, the engine accelerated to a Mach number of 1.45 when a flame-out believed due to spray-bar failure took place. Results regarding time history, pressure recovery, thrust, thrust-minus-drag, and drag coefficient, and comparison with hydrocarbon fuel are provided.

The criteria for selection of an HRT secondary refrigerant system refrigerant to replace Freon-11 are given. The properties of Amsco which make it desirable are tabulated and it is compared with triethyl phosphate (the second choice) and Freon-11.

Memorandum presenting an evaluation of the performance increase resulting from the addition of 20 percent fluorine to the oxygen-RP-1 propellant combination in a 5000-pound-thrust rocket engine at a chamber pressure of 650 pounds per square inch absolute. Runs were made with the engine water cooled and regeneratively cooled.

An investigation of the performance increase resulting from the addition of 20 percent fluorine to the oxygen-RP-1 propellant combination in a 5000-pound-thrust rocket engine at a chamber pressure of 650 pounds per square inch absolute.

Memorandum presenting a full-scale free-jet investigation of a two-shock side-inlet diffuser at Mach umber 2.75 in an altitude test chamber. Data were obtained over ranges of free-stream total pressure and temperature. Results regarding diffuser mass-flow ratio, critical pressure recovery, diffuser static-pressure variation, and diffuser-outlet flow conditions are provided.

Memorandum presenting the effect of missile armament on the performance of an interceptor-type aircraft model at Mach numbers 1.5, 1.7, and 1.9 and at angles of attack up to 19 degrees. The aircraft model was characterized by triangular-shaped normal-shock inlets located at wing roots. Results regarding force measurements, effect of armament on inlet-duct performance, fuselage boundary-layer survey, and total-pressure contours at inlet throat and diffuser exit are provided.

Combustion efficiency of pentaborane fuel in 48- inch diameter ramjet engine.

Report presenting testing of pentaborane as a fuel in a 48-inch-diameter ram-jet engine in a free-jet facility. Each test lasted about 50 seconds and used fast-response instrumentation and prescheduled fuel-flow variation for a range of fuel-air ratios. Results regarding combustion performance, ignition, oxide deposits, and fuel-injector performance are provided.

Report presenting an experimental investigation of a scale model of the forebody of a proposed supersonic fighter to determine the internal performance and configuration drag of various twin-side inlets. External-compression ramp and bump inlets with various types and combinations of boundary-layer bleed were tested. Results regarding performance charts and flow characteristics are provided.

Report presenting a review of the literature on the thermodynamic and physical properties of boric oxide. Data on the following properties is presented: specific heat, sensible enthalpy, total enthalpy, entropy, latent heat of vaporization, and vapor pressure for the crystal, liquid, and vapor states.

A method has been developed for the determination of total sulfur in fluoride salts using the methylene blue procedure. Reduction of sulfate to hydrogen sulfide is achieved through the use of a new reducing mixture consisting of stannous chloride dissolved in concentrated phosphoric acid. The new mixture is effective on microgram amounts of sulfate and offers a major advantage over the red phosphorous reducing mixtures in that larger samples may be taken for analysis. The procedure has been applied to fluoride salts containing from 1 to 500 ppm of sulfur. The coefficient of variation the method is 10 percent.

"The Lewis Flight Propulsion Laboratory of the National Advisory Committee for Aeronautics proposes to build a zero power research reactor facility which will be located in the laboratory grounds near Cleveland, Ohio. The purpose of this report is to inform the Advisory Committee on Reactor Safeguards of the U. S. Atomic Energy Commission in regard to the design of the reactor facility, the characteristics of the site, and the hazards of operation at this location. The purpose of this reactor is to perform critical experiments, to measure reactivity effects, to serve as a neutron source, and to serve as a training tool" (p. 1).

Memorandum presenting a performance investigation using hydrogen fuel in a full-scale afterburner conducted with particular study of fuel-injector configurations and afterburner length. A total of seven fuel-injector configurations, grouped by type as concentric ring or radial bar, were investigated at a specified burner-inlet velocity and range of burner-inlet total pressures.

Report presenting a performance investigation using hydrogen fuel in a full-scale afterburner with particular study of fuel-injector configurations and afterburner length. A total of seven fuel-injector configurations, some concentric ring and some radial bar, were investigated at a specified burner inlet velocity over a range of burner-inlet total pressures.

Combustion blow-out velocities were determined for JP-4 solutions containing: (1) 10 % ethylene - decaborane reaction product, (2) 10% and 20% acetylene - diborane reaction product, and (3) 5.5%, 15.7%, and 30.7% methylacetylene - diborane reaction product. These were compared with blow-out velocities for JP-4, propylene oxide, and neohexane and previously reported data for JP-4 solutions of pentaborane. For those reaction products investigated, the blow-out velocities at a fixed equivalence ratio were higher for those materials containing higher boron concentrations; that is, blow-out velocity increased in the following order: (1) methylacetylene - diborane, (2) acetylene - diborane, and (3) ethylene - decaborane reaction products.

The heat of combustion of the product formed by the reaction acetylene and diborane was found to be 20,100 +/- 100 Btu per pound for the reaction of liquid fuel to gaseous carbon dioxide, gaseous water, and solid boric oxide. The measurements were made in a Parr oxygen-bomb calorimeter, and chemical analyses both of the sample and of the combustion products indicated combustion in the bomb calorimeter to have been 97 percent complete. The estimated net heat of combustion for complete combustion would therefore be 20,700 +/- 100 Btu per pound.

"The net heat of combustion of the product formed by the reaction of diborane with a mixture of acetylene and ethylene was found to be 20,440 +/- 150 Btu per pound for the reaction of liquid fuel to gaseous carbon dioxide, gaseous water, and solid boric oxide. The measurements were made in a Parr oxygen-bomb calorimeter, and the combustion was believed to be 98 percent complete. The estimated net-heat of combustion for complete combustion would therefore be 20,850 +/- 150 Btu per pound" (p. 1).