Report presenting experimental flutter testing at Mach numbers up to 3.0 using cantilever-wing models with 0 to 60 degree sweepback and 60 degree delta-wing models. The main variables explored were the high Mach number and center-of-gravity location on flutter trends. The theoretical results for flutter analyses were noted to be lower than the experimental results.

Report presenting testing of the Republic F-105 at low speeds to determine the results of additional longitudinal stability tests of measurements of the hinge moments and normal force of the all-movable horizontal tail on a model equipped with a supersonic-type elliptical wing-root inlet.

Report presenting testing to determine the longitudinal stability characteristics of the TX-17, the "Short Seven", and the TX-21 special weapons. Dynamic and static stability data are provided for a range of Mach numbers and stagnation-pressure levels.

Report presenting an investigation at free-stream Mach numbers of 1.62, 1.94, and 2.41 to determine the external-drag effects and pumping characteristics of a short ejector housed within a highly bottailed afterbody. The tests covered secondary to primary diameter ratios of 1.50 and 1.33, mass flow ratios from 0 to 0.20, and a sonic and a supersonic primary nozzle. Results regarding drag and pumping characteristics are provided.

Report presenting an experimental investigation in the blowdown tunnel to determine the balancing effects of a detached tab on a constant-chord trailing-edge control mounted on a 60 degree delta wing for a range of Mach numbers. Control hinge moments, rolling moments, and lift effectiveness of the semispan wing-body combination are provided.

Report presenting a program to investigate the aerodynamic characteristics of thin delta wings with symmetrical double-wedge sections in the hypersonic tunnel at a Mach number of 6.9. A family of 5-percent-thick lifting wings with semiapex angles were tested over a range of angles of attack. Results regarding lift and drag characteristics, center of pressure and moment coefficient, Schileren photographs, and surface film flow studies are provided.

From Summary: "An investigation of a 1/21-scale model of the Chance Vought F7U-3 airplane in the combat-loading condition has been conducted in the Langley 20-foot free-spinning tunnel. The recovery characteristics of the model were determined by use of spin-recovery rockets for the erect and inverted spinning condition. The rockets were so placed as to provide either a yawing or rolling moment about the model center of gravity. Also included in the investigation were tests to determine the effect of simulated engine thrust on the recovery characteristics of the model."