"Theoretical values of performance parameters for liquid ammonia and liquid fluorine as a rocket propellant were calculated on the assumption of equilibrium composition during the expansion process for a wide range of fuel-oxidant and expansion ratios. The parameters included were specific impulse, combustion-chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, coefficient of viscosity, and coefficient of thermal conductivity" (p. 1).

"Theoretical values of performance parameters for liquid ammonia and liquid fluorine as a rocket propellant were calculated on the assumption of equilibrium composition during the expansion process for a wide range of fuel-oxidant and expansion ratios. The parameters included were specific impulse, combustion-chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, coefficient of viscosity, and coefficient of thermal conductivity" (p. 1).

Report discussing tests on a helicopter rotor powered by ram-jet engines located at the rotor blade tips. Information about the basic hovering characteristics of the rotor and the propulsive characteristics of the ram-jet engine were obtained over a range of speeds and fuel rates. Results were also obtained in the power-off condition and with the engines removed.

Ignition delays of alkyl thiophosphites were obtained in a modified open-cup apparatus and a small-scale rocket engine apparatus. At -40 F, mixed alkyl thiophosphites gave short delays with white fuming nitric acid containing 2 percent water and red fuming nitric acids of widely varying compositions. At -40 F and higher, triethyl trithiophosphite blended with as much as 40 percent n-heptane gave satisfactory self-igniting properties at temperatures as low as -76 F.

Report presenting the performance of the liquid fluorine-liquid ammonia propellant combination investigated in 100-pound-thrust, water-cooled engines operating at a chamber pressure of 300 pounds per square inch absolute. Several impinging-jet injectors were evaluated in chambers of characteristic length equal to 50 inches. Results regarding specific impulse, characteristic velocity, thrust coefficient, heat rejection, and operational notes are provided.

From Introduction: "Problems associated with the use of aluminum borohydride for ignition in aircraft are discussed. A detailed description of its properties and results of static chamber tests to determine the effect of diluting aluminum borohydride with n-pentane on flammability in dry air are included in this investigation."

From Summary: "The investigation of air-launched ram-jet engines has been extended to include a study of models with a nominal design free-stream Mach number of 2.40. These models require auxiliary thrust in order to attain a flight speed at which the ram jet becomes self-accelerating. A rocket-boosting technique for providing this auxiliary thrust is described and time histories of two rocket-boosted ram-jet flights are presented. In one flight, the model attained a maximum Mach number of 2.20 before a fuel system failure resulted in the destruction of the engine. Performance data for this model are presented in terms of thrust and drag coefficients, diffuser pressure recovery, mass-flow ratio, combustion efficiency, specific fuel consumption, and over-all engine efficiency."

Report presenting experimental damping-in-roll derivatives obtained for a series of 33 swept and tapered wings. The wing plan forms were selected so that a range of leading-edge positions ahead of and behind the Mach cone obtained at three Mach numbers.

Report presenting an analytical investigation to determine the effect of compressor interstage air bleed with the use of constant-area bleed ports on the acceleration characteristics of a typical high-pressure-ratio single-spool turbojet engine. Constant-area interstage bleed, properly located, gave smaller acceleration times than variable-area compressor exit bleed. Results regarding acceleration with interstage bleed, acceleration using constant-area interstage bleed in combination with compressor outlet bleed, variable-area interstage bleed, and comparison of acceleration modes are provided.

Report presenting drag coefficients during power-off transonic flight for the Bell X-1 airplane with a 10-percent-thick wing over a range of Mach numbers and pressure altitudes. The data was compared to an X-1 with an 8-percent-thick wing and a wind tunnel test with a 10-percent-thick wing. Information about necessary angle of attack, drag-rise Mach number, maximum lift-drag ratio, and drag coefficient at zero lift is provided.

Memorandum presenting an investigation of a 14-inch axial-flow-compressor rotor with circular-arc blades operating up to a rotor-inlet relative Mach number of 1.22 in order to determine the blade-element characteristics. Results regarding overall performance, blade-element performance, performance of rotor with guide vanes, performance of rotor alone, and comparison of rotor investigation are provided.