Report discussing testing to determine the static lateral and directional stability and control characteristics of a model of the Republic F-105 airplane. The effects of various vertical tails and ventral fins, wing-tip fences, a canopy fin, fuselage nose shape, external stores, and deflection of horizontal tail, spoiler, and rudder were explored.

Report presenting an investigation to determine the effects of simulated engine nacelles and wing-root freedoms on the flutter characteristics of a cambered, modified, swept, tapered, semispan wing through a range of Mach numbers. Wings were tested with and without nacelles and with the model restrained, free to roll, and free to translate in the vertical direction. Results regarding the effect of nacelles, flutter boundary, and effect of wing-mount freedom are provided.

Report presenting flight and analog-simulator tests with a prototype automatic interceptor in order to study the effects of elevating the radar-boresight axis on the stability and tracking performance of the system. Results regarding effects of interceptor rolling motion upon tracking errors, similarity of flight results and analog-computer results, effect of elevating the radar-boresight axis upon stability, effect of elevating the radar-boresight axis upon the required bank-angle feedback, and application of the principle of elevated radar-boresight axis are provided.

Memorandum presenting an investigation to determine the effects of scale and compressibility on the forces, moments, and pressure distribution on a wing with an aspect ratio of 3 and a taper ratio of 0.5. Lift, drag, and pitching-moment data and the chordwise distribution of static pressure at seven spanwise stations are presented for several sets of Reynolds and Mach numbers. The results indicated that for all Mach and Reynolds numbers in the test range, no apparently flow separation existed near the leading edge of the wing for lift coefficients less than 0.3.

Report presenting an investigation of inlets utilizing two-dimensional compression wedges mounted normal to the fuselage surface with ram-type scoops for partial removal of the boundary layer. Two compression-wedge angles were included to simulate fixed positions of a variable-geometry configuration. Results regarding supersonic performance characteristics and subsonic and take-off performance characteristics are provided.

Memorandum presenting an investigation of the influence of blade-row geometry on secondary flows in a two-dimensional cascade by varying independently stagger angle, aspect ratio, solidity, and angle of attack and by providing blade fillets. Stagger angle and aspect ratio had no appreciable effect on this secondary flow, whereas solidity and angle of attack did affect the flow patterns indicating the turning as a major parameter.

Various methods of providing compressor-capacity and pressure-ratio control in the gas-generator type of compound engine over a range of altitudes from sea level to 50,000 feet are presented. The analytical results indicate that the best method of control is that in which the first stage of compression is carried out in a variable-speed supercharger driven by a hydraulic slip coupling. The constant-speed second stage could be either a mixed-flow rotary compressor or a piston-type compressor. A variable-area turbine nozzle is shown to be unnecessary for cruising operation of the engine.

Report presenting an investigation to determine the damping in yaw and static directional stability characteristics for a flat-fuselage model with its major cross-sectional axis either horizontal or vertical, for a flat-fuselage model with its major axis horizontal in combination with a 45 degree sweptback wing, and for a canard model with a triangular control surface and 45 degree sweptback wing.

Report presenting an investigation to determine the low-speed longitudinal characteristics of an aspect ratio 4 triangular wing alone and in combination with a fuselage, vertical tail, and horizontal tail. The complete model consisted of a wing with a fuselage of fineness ratio 12.5, a thin, triangular, vertical tail, and two thin, unswept, all-movable horizontal tails of two different aspect ratios.

Report presenting an investigation of the performance of a 20-inch-diameter ramjet engine with a high-heat-release pilot burner conducted at zero angle of attack in a free-jet test facility at a Mach number of 3.0. Two flame-holder configurations were used in conjunction with the high-heat-release pilot burner over a range of altitudes. Results regarding the performance of the high-heat-release pilot burner and performance of combustion-chamber configurations are provided.

Report presenting an investigation in the transonic tunnels to determine the aerodynamic force characteristics at low lift coefficients for a 2-percent-thick trapezoidal wing tested in combination with basic and indented bodies. The effects of wing leading-edge droop and wing thickness were investigated. Testing occurred over a range of Mach numbers and angles of attack.

Report presenting flight and analog-simulator tests with a prototype automatic interceptor in order to study the effects of elevating the radar-boresight axis on the stability and tracking performance of the system. The interceptor was designed to perform the lead-pursuit type of attacks and test runs were made in flight and on the analog simulator with and without lead-angle computation. Results regarding the effects of interceptor rolling motion upon tracking errors, similarity of flight results and analog-computer results, effect of elevating the radar-boresight axis upon stability, and application of the principle of elevated radar-boresight axis are provided.

Report presenting an experimental investigation made in the supersonic flutter tunnel to determine the effects of simulated engine nacelles and wing-root freedoms on the flutter characteristics of a cambered, modified, swept, tapered, semispan wing over a range of Mach numbers. Results regarding the effect of nacelles, flutter boundary, and effect of wing-mount freedom are provided.

Report presenting an investigation to study methods for improving the pressure-recovery characteristics of two-dimensional, variable-geometry, supersonic-subsonic diffuser systems. Results without injection, with injection, and effect of diffuser configuration on wind-tunnel performance are provided.

Report presenting the zero-lift drag rise at low supersonic speeds computed by linearized theory for several wing-body-tail combinations and a comparison with experimental data. The results indicate that the computation method is capable of computing the drag rise at low supersonic speeds to an accuracy of about 20 percent.