Suppression control of tonal trailing-edge noise using a plasma actuator

2014 Fiscal Year Final Research Report

• Project/Area Number: 24760664
• Research Category: Grant-in-Aid for Young Scientists (B)
• Allocation Type: Multi-year Fund
• Research Field: Aerospace engineering
• Research Institution: Tokyo Metropolitan University
• Principal Investigator: INASAWA Ayumu 首都大学東京, システムデザイン研究科, 准教授 (70404936)
• Project Period (FY): 2012-04-01 – 2015-03-31
• Keywords: 空力音 / プラズマアクチュエータ / 境界層 / 不安定性

Outline of Final Research Achievements

Suppression control of tonal noise radiation from an airfoil trailing edge is conducted by using a plasma actuator for a NACA0012 airfoil at a chord Reynolds number Re = 220,000. To minimize possible interferences of two-dimensional electrode to the boundary-layer stability, a specially-designed actuator with flush-mounted configuration is employed. It is found that the weak wall jet induced by the two-dimensional actuator can reduce the boundary-layer instability significantly, leading to the efficient suppression control of trailing-edge noise. Suppression of tonal noise is also achieved by weakening two-dimensionality of developing instability waves at the airfoil trailing-edge.

Free Research Field

流体力学