"The rotating multicylinder method for in-flight determination of liquid-water content, droplet size, and droplet-size distribution in icing clouds is described. The theory of operation, the apparatus required, the technique of obtaining data in flight, and detailed methods of calculating the results, including necessary charts and tables, are presented" (p. 1).

Report presenting an investigation in the 4- by 4-foot supersonic tunnel to determine the static longitudinal stability and control characteristics of a supersonic aircraft configuration at a Mach number of 1.59. The model had a 40 degree sweptback tapered wing with 10-percent-thick circular-arc sections normal to the quarter-chord line.

Report presenting testing of two NACA two-blade propellers at a range of blade angles and Mach numbers. The effect of compressibility and design section camber are presented for each propeller. The results indicated that if the outboard sections of a propeller are the thinnest, the design of the propellers should incorporate loading distribution that is concentrated in the tip sections.

Report presenting testing on the first of a series of flutter rockets, designated the NACA FR-1-A, which was tested with two identical swept wings. Results regarding the launching, flight, and wing failure are provided.

Memorandum presenting an investigation in the free-flight tunnel to determine the effect of the sloshing of fuel in partly filled, unbaffled tanks on the lateral stability of a free-flying model. Flight tests were made to determine the effects of the water sloshing for different depths of water and various masses and moments of inertia of the model. The sloshing caused small-amplitude, high-frequency lateral oscillations which were superimposed on the normal Dutch roll oscillation so that the lateral motions of the model appeared jerky.

Report presenting the performance of a ramjet unit consisting of an intake diffuser, an exhaust nozzle, and a cluster of thin-plate burners contained in a semicircular combustion chamber as investigated in the induction aerodynamics laboratory.

"A simple apparatus particularly applicable to the determination of the corrosive effects of flowing liquid metals on structural materials is described. In this apparatus, flow of the liquid medium at known velocities may be induced in toroidal shaped channels fabricated from the test structural material only, with no pump, valves, or flow meter required. A circulating velocity of 25 ft/sec has been obtained in preliminary tests and no basic limitation on increasing the speed was encountered" (p. 1).

Report presenting the results of pressure-distribution and force tests on four wings at Mach number 6.86 and Reynolds number 980,000 in the 11-inch hypersonic tunnel. Characteristics of the wings tested included a 4-inch square plan form, a 5-percent maximum thickness, and diamond, half-diamond, wedge, and half-circular-arc sections. Information about pressure measurements, wing characteristics, and Schlieren photographs is provided.

Report presenting the results from several recent flights on the Northrop X-4 No. 2 airplane, including the longitudinal stability characteristics over a range of Mach numbers in straight and accelerated flight and the short-period longitudinal-oscillation characteristics.

"A camera designed for use in flight has been developed by the NACA Lewis laboratory to photograph cloud droplets in their natural suspension in the atmosphere. A magnification of 32 times is employed to distinguish for measurement purposes all sizes of droplets greater than 5 microns in diameter. Photographs can be taken at flight speeds up to 150 miles per hour at 5-second intervals, A field area of 0.025 square inch is photographed on 7-inch-width roll film accommodating 40 exposures on an 18-foot length" (p. 1).

Memorandum presenting tests made on a normal-shock inlet mounted as a scoop on a flat plate on which a turbulent boundary layer was generated. A boundary-layer-removal scoop was provided between the inlet and the plate and various amounts of the boundary layer were removed. Results regarding the main inlet, boundary-layer scoop, and an evaluation of results are provided.

Report presenting flight testing with two jet-propelled airplanes in rough air to investigate effects of sweep on gust loads and gust selectivity. Data was taken with an unswept-wing airplane and a 35 degree swept-wing airplane for incremental accelerations corresponding to airspeeds of 300 and 450 miles per hour. The results indicated that the swept-wing airplane experienced lower loads in turbulent air than the unswept-wing airplane.

Report presenting measurements of chordwise pressure distributions at four spanwise stations over a 10-percent-thick wing of the Bell X-1 airplane. Results regarding pressure distributions at the various stations and section aerodynamic characteristics are presented. The data was obtained for a range of Mach numbers from 0.30 to 11.9 and altitudes from 17,000 to 47,000 with several different types of maneuvers.

Report presenting an investigation of the flow behind the lifting surfaces of a model equipped with a 60 degree triangular wing and a 60 degree triangular canard tail. Results regarding the force and moment data, air-stream surveys behind the wing, effective values of downwash and dynamic-pressure ratio, effect of tail height and length, a comparison with previous data, the effects of component area and ratio, and the effect of a canard tail are provided.

From Introduction: "This paper will treat the problem in the suggested manner, beginning with the development of a suitable boundary condition to represent mathematically a homogeneous boundary which has the same flow characteristics, at a point in the flow sufficiently removed from the boundary as the actual physical boundary of alternate open and closed portions of the wall. Numerical results will be presented for circular tunnels with uniformly distributed around the circumference, for rectangular tunnels with uniformly distributed around the circumference, for rectangular tunnels with uniformly distributed slots in the top and bottom walls, for rectangular tunnels with the slot distribution determined by a transformation from a uniformly slotted circular tunnel, and for a two-dimensional tunnel. The results of this paper are derived on the basis of an incompressible potential flow."

From Summary: "A free-flight investigation over a Mach number range from 0.6 to 2.0 has been conducted to determine the longitudinal aerodynamic characteristics and effect of rocket jet on zero-lift drag of 1/5-scale models of two ballistic-type missiles, the Hermes A-3A and A-3B. Models of both types of missiles exhibited very nearly linear normal forces and pitching moments over the angle-of-attack range of 8 deg to -4 deg and Mach number range tested."