吸い込みによる後退翼面上の境界層遷移の制御 Control of Boundary Layer Transition on a Swept Wing by Suction
The behavior of three-dimensional boundary layer on swept wings is an important research subject for the future high-speed airplane. The purpose of the present paper is to study controllability of boundary layer transition by suction. Experiments are done by using a closed circuit wind tunnel at Tokai University. The swept wing model with a latch for variable sweep angle at a root is mounted vertically in the 1.5m×1.0m test section. Suction is applied through the perforated surface, and flow velocity of the suction is variable. Two velocity components measured by the twodimensional hot wire anemometer with computer controlled three-dimensional traverse system. At various sweep angles, the velocity inside the boundary layer is measured, and the data are investigated to obtain the relation between the sweep angle and the effect of suction.
- 日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences
日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences 48(563), 393-398, 2000-12-05