From Summary: "Trajectories of water droplets about an ellipsoid of revolution with a fineness ratio of 5 (which often approximates the shape of an aircraft fuselage or missile) were computed with the aid of a differential analyzer. Analyses of these trajectories indicate that the local concentration of liquid water at various points about an ellipsoid in flight through a droplet field varies considerably and under some conditions may be several times the free-stream concentration."

The trajectories of droplets in the air flowing past an NACA 65AO04 airfoil at an angle of attack of 8 deg were determined. The amount of water in droplet form impinging on the airfoil, the area of droplet impingement, and the rate of droplet impingement per unit area on the airfoil surface were calculated from the trajectories and presented to cover a large range of flight and atmospheric conditions. These impingement characteristics are compared briefly with those previously reported for the same airfoil at an angle of attack of 4 deg.

A cylindrical semimonocoque shell of circular cross section was mounted as a cantilever and loaded by a direct shear at the tip. The cylinder was tested with no cutout, with a rectangular cutout on the tension side, and with the cutout centered on the neutral axis on one side of the cylinder. The cutout was successively enlarged through six sizes varying from 30 degrees to 130 degrees in circumference and from 1 and 2 bays in length. Strain measurements were made with resistance-type wire strain gages near the cutout on the stringers, the skin, and the rings for each case, and the stresses obtained are presented in tables. (author).

Report presenting measurements of free-space oscillating pressures near a static propeller in the region where a wing might be located are presented for a range of tip Mach numbers and the results are compared with available theory. The radial pressure distributions vary as a function of axial distance and order of the harmonic. Results regarding free-space pressures and wing pressures are provided.

Report presenting the interaction of a convected field of turbulence with a shock wave, which has been analyzed to yield the modified turbulence, entropy spottiness, and noise generated downstream of the shock. The results in this report are applicable quantitatively to flow in ducts or channels containing normal shocks.

Report presenting temperature recovery factors on a thin-walled, metal, 10 degree included angle cone at a Mach number of 3.12 over a range of angles of attack and Reynolds numbers per foot. An increase in angle of attack was found to increase the equilibrium surface temperatures in the laminar and turbulent boundary-layer regions.

Note presenting a semiempirical study of the bluff-body problem. Some experiments with interference elements in the wake close behind a cylinder demonstrate the need for considering that region in any complete theory.

Note presenting a modification introduced to allow arbitrary separation velocity and base pressure so that values more in conformity with experiment may be chosen. The solution depends on a single base-pressure parameter.

Report presenting an investigation of the longitudinal response characteristics of a swept-wing fighter airplane using normal-acceleration control system. Results regarding the frequency and transient responses, acceleration systems, pitching-velocity command system, and the pitch-attitude system are provided.

Note presenting testing of a woven fiberglass-nichrome wire heater cloth attached directly to the back side of the porous test wall in order to insure exact and known temperature profiles for the injected air. Suction was found to decrease the boundary-layer thickness, increase the magnitude of the friction and heat transfer coefficients, and delay the transition from laminar to turbulent flow.

From Introduction: "Early in 1951 the National Advisory Committee for Aeronautics published, as Technical Note 2276 (ref. 1), a report by the Aluminum Research Laboratories of the Aluminum Company of America on the results of static and fatigue tests of high-strength aluminum alloy monobloc specimens and bolted joints. In view of special interest shown by several aircraft companies, certain expansions of the test program were undertaken by the Aluminum Research Laboratories and are reported herein."

Report presenting a survey of various types of catapults in connection with the problem of accelerating a large car along a track to a speed of 150 miles per hour. A hydraulic jet catapult was found to be the best suited and various design problems of that type are treated. The expected propulsive efficiency of the catapult is given and the effect of a side wind on the jet trajectory is calculated.

Report presenting the results of short-time elevated-temperature creep tests of 75S-T6 aluminum-alloy columns and evaluated with the objective of obtaining procedures for predicting column lifetime. Distortions resulting from creep in objects such as supersonic aircraft and missiles can cause the aerodynamic characteristics to change.

Note presenting the nondimensional lift derivative and the corresponding pitching-moment derivative resulting from constant vertical acceleration as evaluated for a family of thin sweptback tapered wings with streamwise tips traveling at supersonic speeds. The analysis is applicable at those speeds for which the wing leading and trailing edges are both supersonic, provided that the Mach lines from the wing apex intersect the trailing edge and that the Mach line from the leading edge of one tip does not intersect the remote half-wing.

Report presenting charts which permit the rapid estimation of deviations from free-stream values of static pressure, angle of attack, and angle of sideslip so that ideal positions for orifices and vanes for measuring these qualities can be selected. The effects of thickness and angle of attack are considered in greater detail.

Report presenting an account of wind-tunnel measurements at low supersonic speeds of the pressure distribution on a doubly symmetrical double-wedge profile of approximately 8-percent thickness. The results cover a range of Mach numbers, angles of attack, and a specified Reynolds number. Results regarding the characteristics at zero angle of attack, characteristics at angle of attack, comparison with subsonic results, and some general remarks are provided.