"The theoretical performance of pentaborane has been recalculated using recent data on the vapor pressure of boric oxide. Previous calculations were based upon vapor-pressure data obtained some years ago by a method not as accurate as that employed in current investigations. The recalculated performance data for pentaborane differ appreciably from previously published data and are considered more accurate for evaluation of the relative potentialities of boron-containing fuels" (p. 1).

Theoretical calculations of specific impulse to determine the separate effects of increasing the combustion-chamber pressure and the nozzle expansion ratio on the performance of the propellants, hydrogen-fluorine, hydrogen-oxygen, ammonia-fluorine and AN-F-58 fuel - white fuming nitric acid (95 percent). The results indicate that an increase in specific impulse obtainable with an increase in combustion-chamber pressure is almost entirely caused by the increased expansion ratio through the nozzle.

Report presenting an exploratory investigation of the effectiveness of outboard horizontal tails in reducing the static longitudinal stability changes with lift coefficient associated with many sweptback wings. The results indicated that outboard horizontal tails can be a very effective means of counteracting the trend toward longitudinal instability characteristics of many sweptback wings. Results regarding the effects of changes in horizontal-tail position, effects of wing fences, average downwash at the tail, effects of changing tail size, lift, drag, and pitching-moment characteristics, and effects of flaps are provided.

Report presenting several short two-dimensional subsonic diffusers over a range of throat Mach numbers from 0.3 to 0.9. The designs incorporated an effective diffusion angle of approximately 30 degrees and an area ratio of 3. At a throat Mach number of 0.7, the resulting profile distortion of the unmodified 30 degree diffuser was diminished from about 11 to approximately 4 percent by using any of the configurations.

Memorandum describing an investigation using two airplanes, an F6F-3 and F-86A, each fitted with servo equipment for varying in flight the lateral and directional stability and handling characteristics, which have been flown by test pilots to simulate the predicted dynamic behavior of six prototype airplanes. The methods of simulation and the types and ranges of variables considered are presented and the results of the individual programs are discussed.

Report presenting testing of two airplanes, the F6F-3 and F-86A, fitted with servo equipment for varying in flight the lateral and directional stability and handling characteristics and flown by test pilots to simulate the predicted dynamic behavior of six prototype airplanes. Results regarding the aerodynamic characteristics and pilot opinions for each plane are provided.

Report presenting a wind-tunnel investigation to determine the effect of lowering the wing from the top of the fuselage to the bottom of the fuselage on the longitudinal characteristics of a wing-fuselage and a wing-fuselage-tail combination with the horizontal tail at various heights above the plane of the wing. The effects of wing height on the longitudinal characteristics of the model were small.

Report presenting an investigation to determine the effect of lowering the wing from the top of the fuselage to the bottom of the fuselage on the longitudinal characteristics of a wing-fuselage and wing-fuselage-tail combination with the horizontal tail at various heights above the plane of the wing. Testing occurred at a range of Mach and Reynolds numbers.

Report presenting an investigation of the low-speed static lateral stability characteristics of a complete model with a series of M- and W-wings. They were modified from a basic 45 degree swept wing and were designed to cover a range of spanwise locations of the sweep discontinuity.

Report presenting an investigation at low speed in the 300 mph tunnel to determine the static aerodynamic forces and moments on a missile model during simulated launching from 25-percent-semispan and wing-tip locations of a wing-fuselage combination. Results regarding the differences in location and effects induced by the fuselage are provided.

Report presenting a flight investigation at a range of altitudes to determine the wing loads on the Convair XF-92A airplane over the lift range of the airplane at subsonic and transonic speeds. Theoretical lift-curve slope for a delta wing was calculated and compared with the flight data at a Mach number of 0.75.

Memorandum presenting a low-speed wind-tunnel investigation conducted to study the effects of pylon-mounted wing tanks and speed brakes on the static stability characteristics of a model with sweptback wing and tail surfaces. The wing of the model was of aspect ratio 3.45 and was swept 40 degrees at the quarter-chord line. Results for the basic configuration and modifications to the basic configuration are provided.

Memorandum presenting an analysis to determine the compressor pressure ratios and specific weight flows obtainable with single-stage air-cooled turbines for both nonafterburning and afterburning turbojet engines operating at a flight Mach number of 2 in the stratosphere. Wide ranges in turbine-inlet temperature, tip speed, hub-tip radius ratio, and coolant-flow ratio were considered.

Report presenting an investigation of a conservatively designed experimental cold-air turbine with and without a shroud band on the rotor blades. The tip of the rotor blade was oriented toward the tangential direction so that the adverse effect of blade-tip scraping would not be appreciable. The efficiency for the unshrouded-rotor configuration was about one point higher than for the shrouded rotor.

Report presenting an investigation to study the aerodynamic problems associated with a turbine design for a mode of engine operation which utilizes turbine stator adjustment to maintain a fixed compressor operating point. An indication of the turbine requirements for a particular compressor operating point indicated that a feasible sing-stage air-cooled turbine design could be obtained within reasonable aerodynamic limits. Results regarding the performance of the turbine, pressure ratios, and operational requirements are provided.

Report presenting an investigation of combustion oscillations using white fuming nitric acid and a hydrocarbon fuel in a 1000-pound-thrust rocket engine. Results regarding rotary oscillation shown by 40,000-frame-per-second photographs, oscillations recorded by streak photography, ion gap traces, pressure measurements, and plastic chamber erosion are provided.

Report presenting an investigation to increase the compressor surge-limit pressure ratio of the XJ40-WE-6 turbojet engine at high equivalent speeds. An evaluation of the basic redesign of the compressor and 11 additional modifications are examined.

From Summary: "An investigation of the altitude performance of a 20-inch-diameter high-temperature-ratio ram-jet combustor which had been redesigned to provide good combustor efficiency over a wide range of temperature ratios was conducted at zero angle of attack in a free-jet facility at a Mach number of 3.0. Configurations investigated incorporated a cylindrical control sleeve which confined the injected fuel at low over-all fuel-air ratios to about 40 percent of the engine air flow. This provided an optimum fuel-air mixture over a portion of the flame holder when the over-all fuel-air ratio was about 0.02."

Memorandum presenting an icing investigation conducted to determine the general de-icing and runback characteristics of three production samples of electric rubber-clad cyclic de-icing boots. The overall de-icing characteristics of two of the boots investigated were quite similar. Results regarding boot surface temperatures and general de-icing and runback characteristics are provided.

Report presenting an icing investigation conducted in the icing research tunnel to determine the general de-icing and runback characteristics of three production samples of electric rubber-clad cyclic de-icing boots. The boots were all designed for the same airplane and were designed to operate at the same values of power density, heat-on time, and cycle ratio. Results regarding the boot surface temperatures and general de-icing and runback characteristics are provided.

Report presenting visual observations and flow analyses made of annular liquid flow with cocurrent air flow in 2- and 4-inch-diameter horizontal transparent tubes. The experiments occurred over a range of air mass velocities, air temperatures, and Reynolds numbers. Results regarding the velocity and thickness of liquid films, description of water-film disturbances, effect of flow variables on liquid-film characteristics, and relation between disturbances and flow conditions are provided.

Memorandum presenting a systematic study to determine the effect of molecular structure on the flammability limits of pure hydrocarbon-air mixtures at reduced pressures and room temperature. This report presents results obtained for 17 pure normal paraffins, branched paraffins, and mono-olefins. Results regarding experimental variables and experimental observations are provided.

A flight investigation in natural icing conditions was conducted to determine the effect of inlet ice formations on the performance of axial-flow turbojet engines. The results are presented for icing conditions ranging from a liquid-water content of 0.1 to 0.9 gram per cubic meter and water-droplet size from 10 to 27 microns at ambient-air temperature from 13 to 26 degrees F. The data show time histories of jet thrust, air flow, tail-pipe temperature, compressor efficiency, and icing parameters for each icing encounter. The effect of inlet-guide-vane icing was isolated and shown to account for approximately one-half the total reduction in performance caused by inlet icing.

Report presenting testing of a 42.7 degree sweptback tapered wing with three types of ailerons tested at a Mach number of 1.9 and a Reynolds number of 2,200,000; the wing geometry was similar to that of an XS-2 airplane. The purpose of the investigation was to determine the effectiveness of ailerons at these specified flight characteristics. Results regarding the aerodynamic characteristics of the wing are also provided.