University of Tokyo Graduate School
Japan Aerospace Exploration Agency
出版者
宇宙航空研究開発機構
出版者（英）
Japan Aerospace Exploration Agency (JAXA)
雑誌名
宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2006論文集
雑誌名(英)
JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2006
巻
JAXA-SP-06-010
ページ
50 - 55
発行年
2006-12-01
抄録（英）
Flows over a 65-degrees sweep delta wing with a sharp leading edge at various angles of attack and various Mach numbers are computationally studied. Computational simulations show that there are some conditions where the flow fields transit in chordwise direction. There appear three kinds of chordwise transitions of flow fields; (1) vortex breakdown above the delta wing at high angles of attack and subsonic flow conditions, (2) shock wave normal to the chordwise direction at center of the delta wing at high angles of attack and transonic flow conditions, which often accompanies vortex breakdown, and (3) intermediate flow fields that include two different types of flow in chordwise direction in the border area between two different flow types. Computational simulations also show that there is close correlation between breakdown and normal shock wave at the center of the wing at high angles of attack and transonic flow conditions. The results also show that vortex structure and two types of shock wave are related closely each other in the intermediate flow fields in chordwise direction.
様々な迎角・マッハ数におけるデルタ翼周りの流れ場特性コード方向の流れ場変化
63154010.pdf
(1.86MB)
