44th Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2012 (July 5-6, 2012. Toyama International Conference Center), Toyama Japan
抄録（英）
The present paper deals with instability and transition of 3-D boundary layer developing on a yawed circular cylinder with a sweepback of 60 degrees at Mach 2 in the supersonic wind tunnel of Muroran Institute of Technology. Visualized surface flow presents many striations regularly aligned almost to inviscid streamline, while hot-wire survey shows time-dependent broad-band disturbances, both of which originate from the so called cross-flow instability. It is found that comparison of experiments and stability analyses shows good agreement. The effect of condensation in the main flow on static pressure on a 5-degree semi-vertex cone model is discussed.
内容記述
形態: カラー図版あり
内容記述（英）
Physical characteristics: Original contains color illustrations
超音速三次元境界層の進行波モードの検出
61958034.pdf
(1.09MB)
