Modulation and active control of supersonic flow by introducing artificial disturbance

2017 Fiscal Year Final Research Report

• Project/Area Number: 15H02321
• Research Category: Grant-in-Aid for Scientific Research (A)
• Allocation Type: Single-year Grants
• Section: 一般
• Research Field: Aerospace engineering
• Research Institution: Nagoya University
• Principal Investigator: Sasoh Akihiro 名古屋大学, 工学研究科, 教授 (40215752)
• Co-Investigator(Kenkyū-buntansha): 岩川 輝 名古屋大学, 工学研究科, 講師 (70733236)
• Project Period (FY): 2015-04-01 – 2018-03-31
• Keywords: 超音速流れ / 衝撃波 / 乱流 / 境界層

Outline of Final Research Achievements

In this study, we aimed in understanding mechanisms of supersonic flow modulation by artificial disturbances, and in developing their applications to supersonic flight. A counter-driver shock tube with a 120 mm * 120 mm square-cross-section was developed so that experiments of shock wave-turbulence interaction became possible. As a result, it was experimentally demonstrated that the longer the propagation distance the more the shock wave surface became disturbed, thereby leading to the topological transition of the wave front. Moreover, by introducing repetitive laser energy pulses on to Mach 1.9 flow, the shock wave oscillation experienced frequency modulation to a low frequency regime so that total pressure loss was reduced in a supersonic duct.

Free Research Field

航空宇宙工学