"A method of distributing fuel equally to a plurality of spray nozzles in a gas-turbine engine by means of balanced-diaphragm fuel distributors is presented. The experimental performance of three of eight possible distributor arrangements are discussed. An analysis of all eight arrangements is included. Criterions are given for choosing a fuel-distributor arrangement to meet specific fuel-system requirements of fuel-distribution accuracy, spray-nozzle pressure variations, and fuel-system pressures" (p. 1).

Report presenting an investigation at subsonic and transonic speeds to determine the aerodynamic characteristics of three geometrically similar wings with 42 degree sweepback of the leading edge, aspect ratio 4, taper ratio 0.625, and NACA 64(sub)1-112 airfoils. The lift, drag, and pitching-moment characteristics are provided.

Report presenting an investigation of the low-speed longitudinal stability and control characteristics of a scale model of a Bell X-5 airplane design with various leading-edge slat and trailing-edge flap arrangements. A marked increase in stability with increasing sweep angle at low lift coefficients was noted. Results regarding the basic longitudinal characteristics, leading-edge slats, trailing-edge flaps, and longitudinal control are provided.

A report in a series of five that present unanalyzed pressure data obtained in tests of five full-scale propellers with NACA 16-series blade sections. Pressure distributions on the blade sections were measured under operating conditions to determine the aerodynamic characteristics of each blade section. This particular report presents information for nine radial stations of the NACA 10-(3)(049)-033 propeller.

Data are presented showing the penetration characteristics of liquid jets directed approximately perpendicular to a high-velocity air stream for jet-nozzle-throat diameters from 0.0135 to 0.0625 inch, air stream densities from 0.0805 to 0.1365 pound per cubic foot, liquid jet velocities from 168.1 to 229.0 feet per second and a liquid jet density of approximately 62 pounds per cubic foot. The data were analyzed and a correlation was developed that permitted the determination of the penetration length of the liquid jet for any operation condition within the range of variables investigated.

Report presenting an exploratory free-flight investigation at zero lift of several rocket-powered drag-research models with tapered 4-percent-thick wings for a range of Mach numbers. Wings with an aspect ratio of 3.11 and trailing-edge thickness of 0, 1/3 maximum thickness, 2/3 maximum thickness, and 3/3 maximum thickness were tested.

"An investigation has been conducted in the Langley 4- by 4-foot supersonic tunnel to determine the static lateral stability characteristics of a supersonic aircraft configuration at Mach numbers of 1.40 and 1.59. The model had a 40 degree sweptback wing with 10-percent-thick circular-arc sections normal to the quarter-chord line. The results of the investigation indicated high directional stability that decreased with increasing Mach number and positive effective dihedral that was essentially invariant with lift coefficient and Mach number" (p. 1).

Report presenting the damping-in-roll characteristics of three wings with an aspect ratio of 4, a taper ratio of 0.6, an NACA 65A006 airfoil section, and three different sweep angles at a range of Mach numbers and angles of attack. The data were obtained in the 7- by 10-foot tunnel transonic bump by utilizing the twisted-wing technique. Results regarding the damping-in-roll parameter, angle of attack, and lift-curve slope are provided.

"At the request of the Air Materiel Command an investigation was made in the Langley free-flight tunnel to determine the static longitudinal stability and control characteristics of models coupled together in a tandem configuration proposed by All American Airways, Inc. Force tests were made using 1/20-scale models of B-29 end F-80 airplanes to determine the effects of coupling the fighter to the tail of the bomber. The results of the investigation showed that for the bomber alone the aerodynamic center was 0.21 mean aerodynamic chord behind the center of gravity (stable) but that for the tandem configuration the aerodynamic center was 0.09 mean aerodynamic chord forward of the center of gravity, of the combination (unstable)" (p. 1).

"An investigation of the nature of the flow field behind a rectangular circular-arc wing has been conducted in the Langley 9-inch supersonic tunnel. Pitot- and static-pressure surveys covering a region of flow behind the wing have been made together with detailed pitot surveys throughout the region of the wake. In addition, the flow direction has been measured using a weathercocking vane measurements. Theoretical calculations of the variation of both downwash and sidewash with angle of attack using Lagerstrom's superposition method have been made" (p. 1).

"An investigation has been made in the Langley 9- by 12-inch super-sonic blowdown tunnel at Mach numbers of 1.62 and 1.96 of a partial-span body with one tail surface, designed for use on the Hughes Falcon (MX-904) missile. The present paper extends the work reported in NACA-RM-SL50E10. Force and moment data including elevator hinge moment were obtained for the conditions of the tail in the presence of a small segment of the fore-shortened body, in the presence of a semi-span body and attached to a semi-span body, and for the condition of the foreshortened semi-span body alone" (p. 1).