Report presenting tests of a partial-span model of a large bomber-type airplane, which were conducted to provide data on the aerodynamic characteristics of the aileron-tab arrangement and of the wing. Testing occurred to determine the rolling-moment, yawing-moment, and hinge-moment characteristics of the aileron and tab and the effect of midchord wing slots on the characteristics of the wing and aileron and tab. Results regarding the aerodynamic and stalling characteristics of the wing and aerodynamic characteristics of the aileron and tab are provided.

Note presenting measurements of the vertical distribution of liquid water concentration and drop size made in winter stratus clouds in the absence of significant cyclonic or frontal activity. The observations indicate that the clouds are formed by turbulent mixing of the lower layers of the atmosphere, resulting in a region of constant specific humidity and adiabatic lapse rates.

Report presenting an analysis of wind-tunnel data for two types of lateral-control system for large airplanes in order to determine the control-force characteristics and rolling effectiveness of each system. The two types of control systems explored are a spring-tab aileron and a combination spoiler and guide or pilot-aileron arrangement.

Report presenting results for a part of a test program on 24S-T aluminum-alloy flat compression panels with longitudinal formed hat-section stiffeners. This particular part of the program is concerned with panels in which the thickness of the stiffener material is equal to the thickness of the skin. Results regarding the hat-stiffened panels and a comparison of hat-stiffened and Z-stiffened panels are provided.

Note presenting a study to determine the nature of the surfaces formed on hardened steel parts during rubbing, notably on piston rings and cylinders during run-in. The technique of measuring the small amounts of material transferred from one rubbing surface to another by making one radioactive is applied to hardened steel surfaces, both nitrided and non-nitrided, and to chromium-plated steel.

Report presenting testing to investigate the effects of compressibility on a 5-inch-chord NACA 0009-64 airfoil section with a 33.4-percent-chord flap with a nose overhang and an unsealed gap. Flap effectiveness was generally found to increase with Mach number. Results regarding the lift, pitching moment, and hinge moment are provided.

Report presenting the results of an investigation to determine the static-pressure losses and total-pressure distributions of a turbojet inlet screen. The screen was tested in two configurations: one with the vane leading edges square and rough and the other with the vane leading edges rounded. Results regarding the static-pressure-loss coefficient, corrected static-pressure loss, and total-pressure distributions are provided.

Report presenting an investigation made of the angle-of-attack-type loading for an elliptical wing of aspect ratio 4.5 in an attempt to augment existing methods of prediction of finite span angle-of-attack hinge-moment parameters.

Report presenting an experimental investigation conducted to determine the effect of varying rivet diameter and pitch on the compressive strength of flat 24S-T aluminum-alloy panels with longitudinal Z-section stiffeners of the type for which design charts are available.

Report presenting low-aspect-ratio wings with triangular plan form, which are treated on the assumption that the flow potentials in planes at right angles to the long axis of the airfoils are similar to the corresponding two-dimensional potentials. Pressure distributions caused by downward acceleration, pitching, rolling, sideslipping, and yawing are obtained for wings with and without dihedral.

Report presenting a method of designing vaneless diffusers using data given for simple conical diffusers. A family of diffusers with three different cone angles and the same throat height was designed and experimentally studied. A second set of diffusers with varying throats with the best cone angle was also investigated.

"The icing characteristics, the de-icing rate with hot air, and the effect of impact ice on fuel metering and mixture distribution have been determined in a laboratory investigation of that part of the engine induction system consisting of a three-barrel injection-type carburetor and a supercharger housing with spinner-type fuel injection from an 18-cylinder radial engine used on a large twin-engine cargo airplane. The induction system remained ice-free at carburetor-air temperatures above 36 F regardless of the moisture content of the air. Between carburetor-air temperatures of 32 F and 36 F with humidity ratios in excess of saturation, serious throttling ice formed in the carburetor because of expansion cooling of the air; at carburetor-air temperatures below 32 F with humidity ratios in excess of saturation, serious impact-ice formations occurred" (p. 1).

From Summary: "An approximate relation is derived for the surface velocity potential of thin pointed wings at supersonic speeds when they are contained within the Mach cone from the vertex. This relation is applied to obtain the pressure distributions, the lift and drag coefficients, the center of pressure, and the rolling moments as a function of angle of yaw for the delta wing. Theoretical curves are presented for a Mach number of the square root of 2 to illustrate the relations."

Note presenting measurements of the vertical distribution of liquid water concentration and drop size in winter stratus clouds in the absence of significant cyclonic or frontal activity. The observations indicate that the clouds are formed by turbulent mixing of the lower layers of the atmosphere, resulting in a region of constant specific humidity and adiabatic lapse rates. Calculations based on the observations were used to construct a graph that gives the liquid water concentration in terms of the temperature at the cloud base and the height above the base.