"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).

"A study has been made of the variation of seaplane hull weight with length-beam ratio in a systematic series of hulls designed for constant gross weight and similar spray characteristics. It is found that increases in the length-beam ratio bring about small reductions in the hull weight if it is assumed that seaplanes having the same weight and bottom shape will be designed for the same load factor. A short discussion is also given to show the reduction in load factor that may occur with high length-beam ratios" (p. 1).

Report presenting the low-speed longitudinal characteristics of swept wings derived from investigations at high Reynolds numbers. Two different types of flow separation, trialing-edge and leading-edge separation, are identified and discussed.

"An investigation of the jet-spreading characteristics of a 16 inch ram-jet engine was conducted in the 8 by 6 foot supersonic tunnel at a Mach number of 2.0; both a converging nozzle having a contraction ratio of 0.71 and a cylindrical extension to the combustion chamber were used. The jet boundaries determined by means of pitot pressure surveys were compared with boundaries calculated from one-dimensional continuity and momentum relations. For the cylindrical nozzle, the jet reaches its maximum diameter, 4 percent greater than calculated, about 0.6 nozzle-exit diameter downstream of the nozzle exit" (p. 1).

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 was conducted in a 3.4- by 3.4-inch duct to determine the characteristics of the supersonic flow downstream of four wire-mesh screen nozzles with nominal design Mach numbers in the range between 1.97 and 2.58. Two types of disturbances were observed in the flow field: a fine network of interacting expansion and compression waves which were formed immediately downstream of the screens and appeared to dissipate within 25 to 40 wave intersections; and relatively strong oblique shock waves that originated at the junctions of the screens and the walls and were reflected throughout the length of the duct. Regions of fairly uniform flow were found to exist" (p. 1).

Investigation to determine lift, drag, and pitching-moment characteristics of several engine-strut-body combinations was conducted over range of angles of attack from 0 degrees to 10 degrees at Mach numbers of 1.8 and 2.0. The average Reynolds number based on body length was 28x106. Data are presented without analysis and indicate decreases in minimum drag and lift curve slope with decreasing in minimum drag and lift curve slope with decreasing strut length. Decreases in minimum drag also noted with rear-ward movement of engines.

Report presenting testing using a Douglas D-558-I airplane to determine the effect of wing vortex generators on some of the undesirable handling characteristics of aircraft flying at hypercritical speeds. The effects on buffeting, lateral unsteadiness, change in trim, and loss of control effectiveness were the primary objectives.

The performance of a turbojet engine with a two-stage turbine, an adjustable first-stage turbine stator, and a variable-area exhaust nozzle was investigated at selected constant engine speeds and two simulated flight conditions. For the particular component characteristics of the engine investigated, little improvement in thrust levels of interest by use of an adjustable rather than an optimum fixed first-stage turbine stator.

Report presenting an investigation to determine the lateral control characteristics of constant-percent-chord trailing-edge elevons on a tailless wing-body combination with a pointed wing of aspect ratio 2. The effectiveness of inset tabs in reducing the elevon hinge moment was also determined. Results include the lift, drag, pitching moment, rolling moment, elevon hinge moment, tab moment, elevon load, and center of pressure of elevon load.

Report presenting an investigation in the transonic tunnel to determine the influence of a change in body shape on the effects of twist and camber. Twist and camber were found to greatly improve the maximum lift-drag ratios of the wing-modified fuselage configuration through the speed range, but reduced the ratios for a wing-curved fuselage configuration. Results regarding basic aerodynamic data are also provided.

Report presenting an investigation of the feasibility of modifying the transient portion of the stick force in abrupt maneuvers in order to eliminate inadvertent normal-acceleration overshoots. The modification consists of additional stick force proportional to a quantity which leads the normal acceleration. The characteristics introduced by the inclusion of the force were considered to be very desirable by pilots.

Report presenting performance characteristics of three similar canard-type, long-range ram-jet missiles to evaluate the relative merits of several types of engine installation. Some of the engine installations included a twin-engine nacelle-type installation strut-mounted above and below the fuselage, a twin-engine nacelle-type installation mounted on the wing, and a single-engine fuselage-contained installation with an underslung scoop-type inlet.

From Introduction: "The altitude performance characteristics of the prototype J40-WE-8 turbojet engine were determined in the NACA Lewis altitude wind tunnel. The altitude operational characteristics of the engine are presented herein. The results of a brief study of the effect of the two different grades of fuel (MIL-F-5624A grades JP-3 and JP-4) on steady-state engine performance at an altitude of 45,000 feet and a flight Mach number of 0.20 are also given."

Report presenting an investigation of two internal-contraction inlets in the block tunnel. The fixed inlet was tested at Mach number 2.94 with a conventional ram-scoop bleed and a shock-trap bleed. Results regarding the fixed-capture-area inlet and variable-capture-area inlet are provided.

A wind-tunnel investigation of the Boeing XB-47 full-scale empennage was conducted to provide, prior to flight tests, data required on the effectiveness of the elevator and rudder. The XB-47 airplane is a jet-propelled medium bomber having wing and tail surfaces swept back 35 degrees. The investigation included tests of the effectiveness of the elevator with normal straight sides, with a buldged trailing edge, and with a modified hinge-line gap and tests of the effectiveness of the rudder with a normal straight-sided tab and with a bulged tab.

Report presenting a wind-tunnel investigation performed in the high-speed tunnel to study the effect of wing sweep and taper ratio on spoiler-slot-deflector control effectiveness. All of the wings tested were aspect-ratio-4 and had NACA 65A004 airfoil sections as well as a variety of sweep angles, taper ratios, and spoiler projections. The results are presented without analysis.

Report presenting an investigation in the 9- by 9-inch Mach number 4 blowdown jet on a generalized body-wing-tail missilelike configuration to determine the source of the adverse rolling moment due to yaw experienced by this type of configuration with lifting surfaces and ventral and dorsal tail surfaces. Results regarding the longitudinal characteristics and lateral characteristics are provided.

Report presenting an investigation of the internal-flow characteristics of two novel designs of internal-compression air inlets in the supersonic blowdown tunnel. A longitudinally slotted contracting channel and effective contracting channel formed by the natural thickening of the boundary layer in a confined channel can be used to obtain pressure recoveries at a satisfactory level.

"An investigation has been completed in the Langley 20-foot free-spinning tunnel on a 1/24-scale model of the Grumman F11F-1 airplane to determine its spin and recovery characteristics. An interim report, Research Memorandum SL55G20, was published earlier and the present report concludes the presentation of results of the investigation. Primarily, the present report presents results obtained with engine gyroscopic moments simulated on the model. Also, the current results were obtained with a revised larger vertical tail recently incorporated on the airplane" (p. 1).