Memorandum presenting results of a supersonic flutter investigation of three low-aspect-ratio control surfaces. Two controls were all-movable but the third had a fixed cutout. Results regarding the experiments and calculations are provided.

Transonic flutter derivatives for unswept wing control surface configurations determined by pressure cell measurements. The control surfaces were mounted on a wing with an aspect ratio of 3, a taper ratio of 0.6, and a wing-thickness ratio of 0.06. Results regarding aerodynamic balance, vortex generators, splitter-plate configurations, and wedges are provided.

From abstract: "This progress report describes four IBM 704 codes developed and used by UCRL, Livermore, to investigate the motion of any object in the force fields of the sun and any or all of the planets and their satellites."

In this report we present solutions of the design problem in which a system of quadruple lenses is required to carry a particle beam from given focal lines in the x and y planes to other given focal lines. Particular attention will be given to the case of the anastigmatic lens system which takes a beam from one focal point to another focal point. Since the general problem is almost impossibly complicated a simplification is introduced by breaking the lens system into two parts. The first part of the lens system is required to bring the initial beam to the state where it is parallel to the z axis in both planes. The second part carries the initially parallel beam to the required final condition. Each part will involve two quadrupoles so that the complete system will consist of four quadruples; usually, however, the field gradients in the second and third quadrupoles can be made identical so that those quadrupoles can be combined into one and the system becomes a three quadrupole system. The configuration of the lens element will be as shown in the figures below. These figures indicate also the general character of the beam path in the …

Experimental combination hand and shoe counter redesign as a compact, simplified, register readout instrument no larger than the present Five-Fold called Model 2.

Report presenting an investigation in an altitude test chamber using a turbojet engine equipped with an afterburner and ejector to compare directly two techniques of determining thrust that are both applicable to flight installations. One method uses a swinging uncooled rake at the ejector outlet while the other requires extensive instrumentation to measure the momentum forces of systems and the force on the internal surface of the ejector nozzle. Results regarding the swinging-rake technique and internal-pressure technique are provided.

Memorandum presenting an experimental investigation to determine the effect on drag of applying the moment-of-area-rule modifications to wing-body combinations with various wing plan forms. The effect of mounting air-to-air type missiles on the wing-mounted bodies of revolution which are part of the moment-of-area-rule modification was also investigated.

Report presenting a determination of transonic flutter characteristics from pressure cell measurements on control surfaces sinusoidally oscillated at an amplitude of plus or minus 1.08 degrees at frequencies from 5 to 30 cycles per second. Various control-surface configurations were investigated, including internal and external aerodynamic balance, vortex generators, a splitter-plate type of control surface, and superposition of triangular shaped wedges or tetrahedra along the rear portion of the control-surface chord.

Report presenting the results of a supersonic flutter investigation of three low-aspect-ratio control surfaces, two which had all-movable controls and one with a fixed cutout. Experimental results are provided and compared to calculations using the piston theory for plan form 2. Modifications for improving the flutter of the various control surfaces are also described.

"Additional wind-tunnel tests were made of a 1/8-scale model of the Republic XP-91 airplane to determine its characteristics with various modifications. The modifications included a revised conventional tail, revised rocket arrangement, drooped wing tips, and revised landing gear and doors. Tests were also made to determine the effectiveness of the control surfaces of the model with the conventional tail and the effect of changing wing incidence and tail length. The revised rocket arrangement provided a considerable increase in the static directional stability contributed by the vee tail at small angles of yaw" (p. 1).