Studies on the Developments of New Measurement Methods for Supersonic Turbulent Flow and the Clarifications of Mechanisms of Supersonic Turbulence

2014 Fiscal Year Final Research Report

• Project/Area Number: 24560976
• Research Category: Grant-in-Aid for Scientific Research (C)
• Allocation Type: Multi-year Fund
• Section: 一般
• Research Field: Aerospace engineering
• Research Institution: Osaka Prefecture University
• Principal Investigator: SAKAUE Shoji 大阪府立大学, 工学(系)研究科(研究院), 助教 (70244655)
• Co-Investigator(Kenkyū-buntansha): ARAI Takakage 大阪府立大学, 大学院工学研究科, 教授 (10175945) ; NISHIOKA Michio 大阪府立大学, 大学院工学研究科, 客員研究員 (60081444)
• Project Period (FY): 2012-04-01 – 2015-03-31
• Keywords: 航空宇宙流体力学 / 超音速乱流機構 / 超音速乱流境界層 / 超音速混合遷移 / 熱線流速計 / 定量化シュリーレン法 / ３次元PIV

Outline of Final Research Achievements

In the present study, the measurement methods for supersonic turbulent flow that is the fluctuation measurements by the quantitative schlieren method, the calibration method for PIV measurement, and a new-type hot-wire anemometer, are developed. By using these methods, the turbulent transition of supersonic boundary layer and the supersonic turbulent mixing field are examined in detail. For the supersonic boundary layer transition, it is shown that the transition Reynolds number transferred into incompressible flow condition are almost constant irrespective of Mach number. For the supersonic mixing, it is also shown that the small-scale fluctuations generated by the streamwise vortices in supersonic mixing fields decrease as Mach number increase. In addition, a novel diagnostic means is devised to sharply distinguish log-law and power-law mean flow behavior of wall turbulence, and the coexisting phenomena of both distributions in flat plate turbulent boundary layer are clarified.

Free Research Field

航空宇宙流体力学