Report presenting flight test data obtained from a large swept-wing bomber airplane in flight through rough air at 5,000 feet to determine the effects of vertical translation and pitching motions on the angles of attack of the wing and tail. The results indicate that the motions, particularly the pitching motions, significantly amplify the angles of attack of the wing and tail for the test airplane.

Note presenting heat-transfer rates at the stagnation point of 1.0-inch-diameter glass spherical models in shock-tube flows in air which correspond to free-flight conditions between Mach numbers of 6.4 and 13.9 with stagnation temperatures up to 7900 degrees R. The heat-transfer rates were determined from measurements of the surface-temperature change with time of a thin-film-platinum resistance thermometer.

Note presenting a model with an inverted-V transverse shape and a dead-rise angle of -20 degrees as part of a study of hydrodynamic impact loads on chine-immersed bodies. A series of fixed-trim impacts of the inverted-V model were made in smooth water over a wide range of trim and initial flight-path angles at a beam-loading coefficient of 19.15 with a few impacts at beam-loading coefficients of 27.90 and 36.07. The data are presented in tables and in figures as variations of loads and motions (in coefficient form) with time, trim angle, and flight-path angle.

Report presenting a comparison of two different methods of calculating transient temperatures for thick walls with arbitrary variation of heat-transfer coefficient and adiabatic-wall temperature.

Report presenting three compressor rotors with low-cambered 6-percent-thick NACA 65-series blade sections tested at low speeds. The tests were made at three solidities, without guide vanes or stators, over ranges of blade-setting angles and quantity-flow rates. Results regarding the efficiency and pressure-rise coefficients, variation of section turning angle with angle of attack, comparison between low-speed rotor and cascade turning angles, and carpet pots are provided.

Report presenting analytical solutions for the temperature and thermal-stress distributions in thick skins and structural elements such as angle, channel, T-, and H-sections when heated at a constant rate.

Note presenting wind-tunnel calibrations of three types of angle-of-attack sensing devices - the pivoted vane, the differential pressure tube, and the null-seeking pressure tube. Flight data on the position errors for three sensor locations - ahead of the fuselage nose, ahead of the wing tip, and on the forebody of the fuselage - are also presented. Various methods for calibrating angle-of-attack installations in flight are briefly described.

Report presenting an investigation in the 7- by 10-foot tunnel by means of the transonic-bump technique to determine the lift augmentation of several jet-flap configurations. The investigation covered a range of Mach numbers. The results indicated that the lift can be increased at any Mach number by blowing downward through a number of closely spaced holes along and near the trailing edge of the wing.

Note presenting the effect of temperature on Young's modulus of elasticity as determined for 2024-T3 and 7075-T6 aluminum alloys, AZ31A-0 magnesium alloy, RS-120 titanium alloy, and type 303 stainless steel by flexural vibration tests of beam specimens at temperatures from room temperature to 900 degrees Fahrenheit. The test frequencies were varied from 40 to 550 cycles per second.

Note presenting a study of aluminum alloy containing 4 weight percent copper during aging using low-frequency internal-friction measurements in torsional and flexural vibration. Both polycrystalline and single-crystal specimens exhibit an initial internal-friction peak at 173 degrees Celsius after solution treatment and quenching.

Note presenting a brief study of available wind-tunnel data with regard to the variation of pitching moment with sideslip. The results indicate that the effect of sideslip on pitching moment can be large and is dependent on a number of factors. Results regarding wing characteristics, wing-body characteristics, horizontal-tail characteristics, and flat fuselages are provided.

From Summary: "A matrix solution for the spanwise bending moments and deflections of a torsionally rigid rotor blade subjected to an arbitrary loading is presented. The method includes the cantilever, teetering, and hinged blades in hovering and in steady forward flight. The method is comparatively short, involves only standard matrix procedures, and does not require that the mode shapes or natural frequencies be known."

From Summary: "The effectiveness of a magnetic field in stabilizing the laminar flow of an incompressible, electrically conducting fluid is studied. The neutral stability curves pertaining to a two-dimensional sinusoidal disturbance are presented for flow over a semi-infinite flat plate in the presence of either a coplanar or transverse magnetic field and for channel flow in the presence of a coplanar or transverse magnetic field and for channel flow in the presence of a coplanar magnetic field. As is to be expected, the magnetic field stabilizes the flow unless the velocity profile is distorted by the magnetic field to an inherently unstable shape."

Note presenting creep tests performed on coarse-grained ingot iron over a temperature range from 700 to 1350 degrees Fahrenheit to find whether the amount of grain-boundary sliding determined the fracture mode, either transgranular or intergranular. Transgranular fractures were obtained at temperatures below 800 degrees Fahrenheit and stresses above 20,000 psi. It is concluded that a vacancy-condensation mechanism is most probably responsible for high-temperature intergranular fracturing in ingot iron.

Note presenting tests of several noise suppressors consisting of combinations of mixing nozzles and ejectors on two full-scale turbojet engines. Maximum sound pressure level reductions of 12 decibels and sound power level reductions of 8 decibels were obtained. Acoustic results, jet mixing, and engine performance are provided.

Report presenting an investigation of the mechanism by which the addition of boron and zirconium improves the creep-rupture properties of an alloy of 55 percent nickel, 20 percent chromium, 15 percent cobalt, 4 percent molybdenum, 3 percent titanium, and 3 percent aluminum at 1600 degrees Fahrenheit. The creep-rupture properties were improved because the boron and zirconium have a pronounced stabilizing effect on the grain boundaries of the alloy. Results regarding the microstructures in initial condition, changes in microstructure during exposure at 1600 degrees Fahrenheit, interpretation of other microstructural changes, relation of mechanism to published information, causes of effect of boron and zirconium on grain-boundary stability, role of carbon, and generality of results are provided.

From Introduction: "The present report presents the derivation of a simple equation for blade-wake mometum thickness as a function of suction-surface diffusion ratio based on the one-dimensional boundary-layer mometum equation in conjunction with simplifying approximations."

Note presenting a reexamination of the flow and heat transfer about a rotating isothermal disk to include the effects of compressibility and property variations. Results regarding velocities, temperatures, heat transfer, and skin friction and torque, are provided.

"In the approximately isotropic velocity and temperature fluctuation fields behind a hot grid, measurements were made of fluctuation levels and of various double and triple correlation functions. The double and triple correlation coefficient functions are of roughly the same spatial extent for the vector and scalar fields. As anticipated from theoretical considerations, the temperature fluctuations die out more slowly than does the turbulence" (p. 1).

Report presenting an investigation to determine the effects of an inverse-taper leading-edge flap on the drag and static-longitudinal characteristics of a swept-wing-body combination. Testing was carried out in order to maximize the subsonic lift-drag ratios with minimum penalty to the supersonic capabilities of the airplane. Results regarding drag characteristics and lift and pitching-moment characteristics are provided.

Report presenting an investigation in the 5- by 5-inch transonic test section to determine the wave attenuating capabilities of a variety of perforated-wall configurations with and without the use of outflow. Test results indicated that reflected disturbances could be minimized by either varying the outflow through walls of constant porosity or by varying the wall porosity at constant low outflow.

"Aerodynamic forces and moments associated with flapping oscillations of finite wings at low speeds are considered. A comparison of theoretical and experimental results is made for a rectangular wing of aspect ratio 2. Calculated results are also given for three tapered wings of aspect ratio 3 with varying amounts of sweepback" (p. 1).

Note presenting an investigation of the influence of solid-body rotation on a screen-produced turbulence in a flow between concentric, rotating cylinders. Radial distributions of the three components of turbulence intensity and the three turbulent shear stresses were measured at a fixed distance downstream of the screen both with and without rotation.