Report presenting an investigation to determine the overall performance of the three-stage turbine from the J71 turbojet engine. The turbine operated with a maximum brake internal efficiency of approximately 0.84 at an equivalent overall pressure ratio of approximately 3.6 and an equivalent rotor speed of about 110 percent of the equivalent design value.

Report presenting aerodynamic and icing investigations on a model of a turbojet-engine nacelle in order to provide icing protection for the engine, protective screen, and accessory housing by the introduction of hot gases into the inlet-air stream. Adequate ice protection was afforded when the minimum kinetic temperature in the protective screen was greater than 32 degrees Fahrenheit.

"An investigation was conducted in the NACA Lewis altitude wind tunnel to improve the altitude performance and operational characteristics of an afterburner primarily by modifying the diffuser-exit velocity profile by changes in diffuser design and by changing the fuel distribution and the flame holder. Twenty configurations, consisting of combinations of six diffuser geometries, six flame-holder types, and twelve fuel systems, were investigated. Data were obtained over a range of afterburner fuel-air ratios at diffuser-inlet total pressures from 2750 to 620 pounds per square foot" (p. 1).

"As one phase of a comprehensive canopy load investigation, conventional front and rear sliding canopies which are typified by installation on the SB2C-4E airplane, were tested in the Langley full-scale tunnel to determine the pressure distributions and the aerodynamic loads on the canopies. A preliminary analysis of the results of these tests is presented in this report. Plots are presented that show the distribution of pressure at four longitudinal stations through each canopy for a range of conditions selected to determine the effects of varying canopy position, yaw, lift coefficient, and power" (p. 1).

Report presenting an examination of the characteristics of variable-area and fixed-area atomizing nozzles in relation to use in aircraft gas-turbine engines. A variable-area fuel nozzle and a fuel-distribution control that were used int eh experimental operation of a turbojet engine are described. Results regarding nozzle characteristics and fuel distribution, effect of atomization on engine operating characteristics, and fuel-system characteristics during engine operation are provided.

Report presenting a wing-body combination with a plane tapered wing of aspect ratio 3.1, taper ratio of 0.39, and 3-percent-thick, rounded-nose sections in streamwise planes at subsonic and supersonic Mach numbers. The lift, drag, and pitching moment are presented for a range of Mach numbers and Reynolds numbers.

Report presenting theoretical performance characteristics and estimates of effective specific impulse and weight for rocket engines serving a main and booster power plants for missiles. The fuels used included ammonia-fluorine and JP4-oxygen propellants. At extremely high altitudes, the specific impulse depends primarily on the expansion ratio.

Memorandum presenting an investigation on NACA 64(sub 1)-012 and 64(sub 1)A012 airfoils at a range of Mach numbers and low Reynolds numbers, which indicated that the effect of increasing the trailing-edge angle was inappreciable on the Mach number for the normal-force break, to decrease the normal-force-curve slope, to reduce the effects of compressibility, and to decrease the minimum drag coefficient and to increase maximum normal-force to drag ratio.

Report presenting an investigation to determine the effects of vertical location of the wing and horizontal tail on the static lateral and directional stability at various combined angles of attack and sideslip for a supersonic airplane configuration at Mach numbers of 1.41 and 2.01. The configurations investigated included a high-wing, midwing, and low-wing arrangement in combination with horizontal-tail positions varying from a location of 0.208 wing semispan below to 0.556 semispan above the body center line.

Report presenting an investigation of a basic wing-fuselage combination with several types of external-store installations meant to delay the advent of airplane buffet caused by external stores. Modifications for airplane design in order to minimize the effect of drag are provided. Some of the arrangements tested included the tandem-mounted arrangement, flush-mounted arrangement, store with a fan-shaped tail, and auxiliary airfoil arrangement.

Report presenting testing of several turbojet engines with both constant- and variable-area nozzles to extend full-scale nozzle performance to higher exhaust-nozzle pressure ratios and to investigate the effects of constant- and variable-area nozzles on turbojet-engine operation. Results regarding the different types of nozzles are provided.

Report presenting measurements of average heat-transfer and friction coefficients for air flowing through a smooth, electrically heated tube with a bellmouth entrance with a length-to-diameter ratio of 15 and a range of average surface temperatures, Reynolds numbers, exit Mach numbers, and heat fluxes. Results regarding the axial-wall-temperature distribution, heat balance, correlation of heat-transfer coefficients, and correlation of friction coefficient are provided.

Report presenting an investigation to determine the roll effectiveness, hinge-moment characteristics, and aileron center-of-load locations on an outboard 40-percent-semispan flap-type aileron on a 30 degree sweptback wing with an aspect ratio of 3.0, a taper ratio of 0.2, and NACA 65A004 airfoil sections. Results regarding general aileron characteristics and other aerodynamic characteristics are also presented.

From Introduction: "The supersonic axial-flow compressor, for example, appears to offer advantages of high stage pressure ratio and height weight flows (reference 1) but problems peculiar to this compressor type have accompanied its introduction. For high single-stage pressure ratios (>4) the problem of converting the high dynamic energy to useful pressure arises (reference 2). In addition, the high tip speeds and weight flows combine to create a difficult situation for the turbine designer."

"A light-source power unit has been developed that provides reliable trigger, and easy synchronization with rotating elements or electric impulses. When used with conventional spark gaps and flash tubes, this power unit provides a light pulse of high intensity and short duration" (p. 1).