From Introduction: "V-g records supplied the NACA by the Bureau of Aeronautics in 1948 and 1949 have provided additional material. These records are analyzed statistically in this report to the frequency of large values of acceleration and airspeed, and results are compared with the design requirements."

An investigation was conducted in the NACA Lewis altitude wind tunnel to determine the effect of compressor-outlet bleedoff on the performance of an axial-flow turbojet engine equipped with a variable-area exhaust nozzle. Results presented indicate the effect of compressor-outlet bleedoff on performance at altitudes of 25,000 and 40,000 feet and a flight Mach number of 0.53. Variation of performance with bleedoff flow is indicated for operation with fixed- and variable-area exhaust nozzles. Temperature and pressure losses through the bleedoff ducting system are also discussed.

Report presenting ram-recovery and mass-flow ratios for submerged inlets at four positions on the fuselage of a model of a hypothetical fighter airplane. Results related to the inlet location and effect of angle of attack are also provided.

Report of an investigation into the effect of leading-edge radius on the high-speed aerodynamic characteristics of a symmetrical, 9-percent-thick airfoil using three different airfoils at several Mach and Reynolds numbers. Information about the normal-force coefficients, drag coefficients, moment coefficients about the quarter chord, pressure-distribution diagrams, Schileren photographs, and a comparison with data obtained in other tunnels is included.

"Results are presented of an investigation to determine the pressure distributions on a wing with leading-edge sweepback decreasing from 45 degrees at the root to 20 degrees at the tip, an aspect ratio of 4.12, taper ratio of 0.36, and NACA 64A009 airfoil section. Tests were conducted at a Reynolds number of 3.5 x 10(exp 6) and a Mach number of 0.07 on the wing with and without 0.20 chord and 0.65 span split flaps deflected 60 degrees. These pressure distributions are analysed herein to determine the character of flow and its effect on the stability of the wing" (p. 1).

Report presenting testing of a 6.5-inch-diameter ramjet engine with a design Mach number of 2.13 and a short-flame-length combustor. Performance characteristics are provided for a range of Mach numbers and fuel-air ratios. Results regarding thrust, drag tests, static pressure, and combustion efficiencies are provided.

In the determination of the performance of an air-cooled turbine, the cooling-air-flow characteristics between the root and the tip of the blades must be evaluated. The methods, which must be verified and the unknown functions evaluated, that are expected to permit the determination of pressure, temperature, and velocity through the blade cooling-air passages from specific investigation are presented.

Report presenting five fuels of boiling temperatures and several hydrocarbon types in a jet-propulsion annular combustor to determine the effect of fuel boiling temperature and paraffinic and aromatic hydrocarbon types on combustion efficiency and altitude operational limit. At the severe inlet-air condition, the highest combustion efficiencies were obtained with the paraffinic and aromatic fuels with low boiling temperatures were found to vary from 30 to 58 percent.

Memorandum presenting the low-speed lateral control characteristics of a 32 degree sweptforward wing of aspect ratio 5.8 and NACA 65-series airfoil sections as determined in the 19-foot pressure tunnel. The investigation include the measurement of the hinge-moment and normal-force characteristics of an aileron and the rolling-effectiveness characteristics of the aileron and several configurations of spoilers.

Report presenting results from a tank investigation of a powered dynamic model of the Grumman JRF-5 airplane fitted with a single hydro-ski and extended afterbody. Results indicated that the afterbody extension in place of a tail ski reduced the maximum resistance by 10 percent. Removal of the wing-tip skids gave a further reduction in maximum resistance of 3 percent.

Report presenting an attempt to determine the reliability and calibration of the Langley transonic tunnel in the open slotted test section. Results regarding test-section calibration, including flow uniformity, calibration, and angularity, model testing and boundary interference, and reduction of interference are provided.

Report presenting rolling effectiveness and drag tests of spoilers on unswept wings over a range of Mach numbers using rocket-propelled test vehicles in free flight. The wings tested had an aspect ratio of 3.7, were unswept and untapered, had thickness ratios of 3, 6, and 9 percent, and covered a range of flexibilities. Results regarding the rolling effectiveness and drag are provided.

Report presenting results of pressure-distribution measurements at low speed on a wing-fuselage combination with a wing of W plan form with aspect ratio 6, 45 degrees sweep, taper ratio 0.6, and an NACA 65A009 airfoil section placed parallel to the plane of symmetry. Results regarding aerodynamic characteristics, pressure distribution on the wing, pressure distribution on the fuselage, aerodynamic section characteristics, and stall patterns are provided.

Report presenting a low-speed investigation in the stability tunnel to determine the static longitudinal stability and control characteristics of two wing-fuselage combinations equipped with wing-tip controls of half-diamond and half-delta plan form. Results regarding the effect of control area and plan form on control characteristics and on trim characteristics are provided.

Memorandum presenting tests in the 9-inch supersonic tunnel to investigate the factors that determine the magnitude of the wing-tail interference effects on the static longitudinal stability of supersonic missile configurations with low-aspect-ratio, tandem, cruciform lifting surfaces and to develop a missile configuration with a minimum variation in static margin due to wing-tail interference effects.

Report presenting an investigation of three air inlets designed for use at transonic speeds conducted in the 8-foot high-speed tunnel. The basis of the design of the inlets was the use of a nose which was shaped so that substream velocities are maintained on its surface for high-speed operating conditions. Results regarding impact pressure recovery, external pressure distributions, wake-survey drag, supersonic external pressure drag, and design considerations are provided.

Report presenting an investigation of a model of an ejectable pilot seat combination with and without stabilizing fins. The main purpose of the investigation was to determine the static aerodynamic characteristics and effectiveness of various stabilizing fins at a high subsonic Mach number. Results regarding stability and force characteristics for the combinations are provided.

Report presenting an investigation by the wing-flow method to determine the snaking characteristics of a scale partial-model of a research airplane. Additionally, the snaking characteristics of 11 modified configurations of the research-airplane model were determined as well as a model that had a greater fineness ratio.

Report presenting pressure fluctuations measured near the trailing edge of the wing and near the leading edge of the tail of a scale model of the X-1 airplane with a 10-percent-thick wing in the 16-foot transonic tunnel. Results regarding frequency analyses are also provided.

Memorandum presenting an investigation in the Lewis laboratory to obtain pressure-drop data for flow of air with no heat addition through mockups of two reactor segments of the proposed GE aircraft reactor. Pressure-drop data were obtained over a range of Reynolds numbers, air inlet Mach numbers, inlet pressure, and ambient air temperatures. The results indicate that the friction factors, corrected for entrance, vena contracta, momentum, and exit losses are considerably higher at high Reynolds number than those reported for turbulent flow in smooth pipes.

Report presenting boundary-layer measurements on rocket-powered free-flight models to determine average skin-friction coefficients. The test body, NACA RM-10, was a fin-stabilized parabolic body of revolution of fineness ratio 12.2 with a blunt base to provide space for a rocket jet. Results regarding the skin-friction and boundary-layer profiles and experimental and theoretical curves are provided.

Report presenting an analysis of a number of free-flight transient responses resulting from small stabilizer movements obtained during testing of the Bell X-1 airplane to obtain its longitudinal stability characteristics. A comparison of flight data and model test data is also provided.

Memorandum presenting the results of a theoretical investigation of the lateral response and stability characteristics of the X-3 research airplane (Douglas Model No. 499D). Included are time histories calculated by a computer showing the effect of various disturbances on the lateral response of the airplane with 0 degrees geometric dihedral and -5 degrees dihedral.

Memorandum presenting lift, drag, and pitching-moment data and some static rolling-moment data are presented for missile configurations having wing-tail-span ratios equal to and less than 1. The configurations include variations in wing and tail plan forms, wing-tail-span ratios, body length, and nose shape.