Abstract:
Oscillatory heave and pitch derivatives have been determined experimentally and theoretically for a set of eight planforms - three cropped delta wings, three arrowhead wings, and two unswept tapered wings. Three experimental procedures of widely different type were used. These were a free oscillation technique for a wall-mounted half-span wind-tunnel models. A similar technique for models mounted on rocket-b0osted test vehicles and an inexorable forcing technique of the internal rigid drive type applied to half-span wind-tunnel model wings. The theoretical values were obtained by various forms of lifting-surface theory. All these results are tabulated and compared. They cover a Mach number range of approximately 0.8 to 2.5. Some theoretical values of control-surface derivatives are included in the TableS, and a few other miscellaneous experimental or theoretical results are also described.
