ロールするデルタ翼の非定常空力特性 [in Japanese] Unsteady Aerodynamic Characteristics on Rolling Delta Wings [in Japanese]
Access this Article
Search this Article
Vortex flows over rolling delta wings were investigated by flow visualization with oil mist and smoke wire. Compared flow visualization results with force measurements, unsteady aerodynamic characteristics of delta wing were analyzed. Experiments were conducted for two delta wing models with 14 and 7 degree apex half angles, which were forced to oscillate sinusoidally in roll. On the 7 degree apex half angle model, splitting of leading-edge separated vortices were observed in wing roll motion at high angles of attack. Disposition changes of leading-edge separated vortices by splitting induced ta wavy and complicated rolling moment hystagram. The vortex splitting on the slender delta wing is phenomenologically similar to the alternating vortex shedding on the ogive cylinder and to the trailing vortex on the conventional wing trailing-edge.
- JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 47(543), 165-173, 1999-04
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES