Numerical simulations of separated flows around oscillating airfoil for dynamic stall phenomena

Shigeru Aso, Atsuhiro Sakamoto, Masanori Hayashi

Research output: Contribution to conferencePaper

Abstract

Dynamic stall phenomena have been investigated numerically by solving incompressible Navier-Stokes equations with a third- order upwind scheme in order to reveal the flow structure and mechanism of dynamic stall. The separated flows around a wing section at static attack angle are calculated and compared with the experiments which are conducted by the present authors. The Results show excellent agreements with the experiments and the numerical scheme is proved to work well. Separated flows around oscillating airfoil in pitch are calculated by using the scheme and a moving mesh system. The flow conditions are selected from our experiments. The calculated separated region is small in pitching-up process and it becomes large in a pitching-down process. Quite different characteristics of flow patterns between in a pitching-up and pitching-down processes are obtained.

Original languageEnglish
DOIs
Publication statusPublished - Dec 1 1991
EventInternational Pacific Air and Space Technolgy Conference, IPAC 1991 - Nagoya, Japan
Duration: Oct 7 1991Oct 7 1991

Other

OtherInternational Pacific Air and Space Technolgy Conference, IPAC 1991
CountryJapan
CityNagoya
Period10/7/9110/7/91

All Science Journal Classification (ASJC) codes

  • Automotive Engineering
  • Safety, Risk, Reliability and Quality
  • Pollution
  • Industrial and Manufacturing Engineering

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    Aso, S., Sakamoto, A., & Hayashi, M. (1991). Numerical simulations of separated flows around oscillating airfoil for dynamic stall phenomena. Paper presented at International Pacific Air and Space Technolgy Conference, IPAC 1991, Nagoya, Japan. https://doi.org/10.4271/911991