Coning Motion, Autorotation, and Vortice Systems of Slender Missiles . Kegelpendelung, Autorotation und Wirbelsysteme Schlanker Flugkoerper

摘要

The coning motion of missiles with slenderness ratio between 15 and 20.5 was tested in a subsonic wind tunnel at a speed of 34.2 meters per second and a Reynolds number (with body diameter D) of 110,000. It was found that if the longitudinal axis of the model is rotated about its fixed center of gravity, the model describes a conical surface with the coning frequency constant. The coning motion begins with theta L/D between 4.7 and 5.0 and is stabilized with theta L/D between 7.1 and 7.8 with the cone half angle theta constant. The coning motion, as well as the autorotation, which occured were found to be related to the behavior of the vortices shed by the body with the same L/D values. It was also found that the coning motion could be avoided by asymmetrically disturbing the boundary layer. (Author)