Investigation of interaction effect between a three-dimensional boundary layer and a streamwise vortex in a transonic flow using particle image velocimetry specialized for boundary layer measurement

2016 Fiscal Year Final Research Report

• Project/Area Number: 15K17979
• Research Category: Grant-in-Aid for Young Scientists (B)
• Allocation Type: Multi-year Fund
• Research Field: Fluid engineering
• Research Institution: Japan Aerospace EXploration Agency
• Principal Investigator: Koike Shunsuke 国立研究開発法人宇宙航空研究開発機構, 航空技術部門, 研究開発員 (40547064)
• Research Collaborator: KUSUNOSE Kazuhiro ; SATO Mamoru ; KATO Hiroyuki ; ITO Yasushi
• Project Period (FY): 2015-04-01 – 2017-03-31
• Keywords: ボルテックスジェネレータ / 衝撃波 / 遷音速流れ / 境界層 / はく離 / 縦渦 / バフェット

Outline of Final Research Achievements

Modern aircrafts fly at the speed of transonic which is a little lower than sonic speed. On this condition, a strong compression wave, a shock wave, sometimes appears and vibrates on　the wing because of the turbulence and the change of the flight condition caused by collision avoidance and so on. Since the shock wave vibration is harmful for the aircraft safety, we investigated small vanes, vortex generators (VG), that have ability to suppress the shock wave vibration.
Wind tunnel experiments were conducted to validate the numerical simulation which showed the influence of the wing sweep angle on the VG’s effect. The velocity distributions around a shock wave and a vortex were measured using a particle image velocimetry. The results clearly showed the large low speed region on the up-wash side of the vortex when the wing had no sweep angle. It partially validates the result of the numerical simulation.

Free Research Field

流体工学