RESEARCH ON DELTA WING UNSTEADY HIGH ANGLE OF ATTACK AERODYNAMICS

Research Project

Project/Area Number	06452343
Research Category	Grant-in-Aid for Scientific Research (B)
Allocation Type	Single-year Grants
Section	一般
Research Field	Aerospace engineering
Research Institution	The University of Tokyo
Principal Investigator	SATO Junzo The University of Tokyo Graduate School of Engineering, Professor, 大学院・工学系研究科, 教授 (80011211)
Co-Investigator(Kenkyū-buntansha)	TATSUMI Kaoru The University of Tokyo Graduate School of Engineering, Assistant, 大学院・工学系研究科, 助手 (40236550) SUNADA Yasuto The University of Tokyo Graduate School of Engineering, Assistant, 大学院・工学系研究科, 助手 (50216488) RINOIE Kenichi The University of Tokyo Graduate School of Engineering, Associate Professor, 大学院・工学系研究科, 助教授 (20175037)
Project Period (FY)	1994 – 1996
Project Status	Completed (Fiscal Year 1996)
Budget Amount *help	¥7,400,000 (Direct Cost: ¥7,400,000) Fiscal Year 1996: ¥700,000 (Direct Cost: ¥700,000) Fiscal Year 1995: ¥2,400,000 (Direct Cost: ¥2,400,000) Fiscal Year 1994: ¥4,300,000 (Direct Cost: ¥4,300,000)
Keywords	Delta wing / Vortex / High Angles of Attack / Unsteady Aerodynamics
Research Abstract	This research is to study the basic physical details of the fluid dynamic phenomena associated with the wing rock observed at hjgh angles of attack on delta wings. A specially designed forced roll oscillation method with a two-components balance was introduced to take the aerodynamic force and moment ; not adopting the conventional free rotation methods. The success of the method depends on the accurate separation of the inertial and aerodynamic forces from the measurement. Use of light weight models, low rate of oscillation and elaborate calibration of balances made it possible to get data up to the non-dimensional roll rate of 0.1. Two delta wing models of 14 and 7 degree semi-apex angle, respectively, are put to the tests and the model with a smaller apex angle shows very complicated aerodynamics. The reason of these changes are mode clear in relation to the vortex breakdown and vortex splitting by comparing the blance outputs with the flow visualization pictures.