期刊
JOURNAL OF FLUIDS ENGINEERING-TRANSACTIONS OF THE ASME
卷 140, 期 7, 页码 -出版社
ASME
DOI: 10.1115/1.4039233
关键词
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资金
- Natural Sciences and Engineering Research Council (NSERC)
- Southern Ontario Smart Computing Innovation Platform (SOSCIP)
- Ontario Graduate Scholarship (OGS) program
- Canada Foundation for Innovation under the Compute Canada
- Government of Ontario
- Ontario Research Fund-Research Excellence
- University of Toronto
- Federal Economic Development Agency of Southern Ontario
- IBM Canada Ltd.
- Ontario Centres of Excellence
- Mitacs
The shear layer development for a NACA 0025 airfoil at a low Reynolds number was investigated experimentally and numerically using large eddy simulation (LES). Two angles of attack (AOAs) were considered: 5 deg and 12 deg. Experiments and numerics confirm that two flow regimes are present. The first regime, present for an angle-of-attack of 5 deg, exhibits boundary layer reattachment with formation of a laminar separation bubble. The second regime consists of boundary layer separation without reattachment. Linear stability analysis (LSA) of mean velocity profiles is shown to provide adequate agreement between measured and computed growth rates. The stability equations exhibit significant sensitivity to variations in the base flow. This highlights that caution must be applied when experimental or computational uncertainties are present, particularly when performing comparisons. LSA suggests that the first regime is characterized by high frequency instabilities with low spatial growth, whereas the second regime experiences low frequency instabilities with more rapid growth. Spectral analysis confirms the dominance of a central frequency in the laminar separation region of the shear layer, and the importance of nonlinear interactions with harmonics in the transition process.
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