Effects of distributed leading-edge roughness on aerodynamic performance of a low-Reynolds-number airfoil: an experimental study
ABSTRACT: Distributed leading-edge (LE) roughness could have significant impact on the aerodynamic performance of a low-Reynolds-number (low-Re) airfoil, which has not yet been fully understood. In the present study, experiments were conducted to study the effects of distributed hemispherical roughn...
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| Format: | Article |
| Language: | English |
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Elsevier
2018-05-01
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| Series: | Theoretical and Applied Mechanics Letters |
| Online Access: | http://www.sciencedirect.com/science/article/pii/S2095034918301107 |
| _version_ | 1828884195774038016 |
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| author | Yan Zhang |
| author_facet | Yan Zhang |
| author_sort | Yan Zhang |
| collection | DOAJ |
| description | ABSTRACT: Distributed leading-edge (LE) roughness could have significant impact on the aerodynamic performance of a low-Reynolds-number (low-Re) airfoil, which has not yet been fully understood. In the present study, experiments were conducted to study the effects of distributed hemispherical roughness with different sizes and distribution patterns on the performance of a GA (W)-1 airfoil. Surface pressure and particle image velocimetry (PIV) measurements were performed under various incident angles and different Re numbers. Significant reduction in lift and increase in drag were found for all cases with the LE roughness applied. Compared with the distribution pattern, the roughness height was found to be a more significant factor in determining the lift reduction and altering stall behaviors. It is also found while the larger roughness advances the aerodynamic stall, the smaller roughness tends to prevent deep stall at high incident angles. PIV results also suggest that staggered distribution pattern induces higher fluctuations in the wake flow than the aligned pattern does. Results imply that distributed LE roughness with large element sizes are particularly detrimental to aerodynamic performances, while those with small element sizes could potentially serve as a passive control mechanism to alleviate deep stall conditions at high incident angles. Keywords: Distributed roughness, Surface pressure, Particle Image Velocimetry, Aerodynamic stall, Flow separation |
| first_indexed | 2024-12-13T11:03:25Z |
| format | Article |
| id | doaj.art-1578cedbd5d64fff8c12b5723bc41d1a |
| institution | Directory Open Access Journal |
| issn | 2095-0349 |
| language | English |
| last_indexed | 2024-12-13T11:03:25Z |
| publishDate | 2018-05-01 |
| publisher | Elsevier |
| record_format | Article |
| series | Theoretical and Applied Mechanics Letters |
| spelling | doaj.art-1578cedbd5d64fff8c12b5723bc41d1a2022-12-21T23:49:10ZengElsevierTheoretical and Applied Mechanics Letters2095-03492018-05-0183201207Effects of distributed leading-edge roughness on aerodynamic performance of a low-Reynolds-number airfoil: an experimental studyYan Zhang0Corresponding author; Department of Mechanical Engineering, North Dakota State University, Fargo, ND 58108, USAABSTRACT: Distributed leading-edge (LE) roughness could have significant impact on the aerodynamic performance of a low-Reynolds-number (low-Re) airfoil, which has not yet been fully understood. In the present study, experiments were conducted to study the effects of distributed hemispherical roughness with different sizes and distribution patterns on the performance of a GA (W)-1 airfoil. Surface pressure and particle image velocimetry (PIV) measurements were performed under various incident angles and different Re numbers. Significant reduction in lift and increase in drag were found for all cases with the LE roughness applied. Compared with the distribution pattern, the roughness height was found to be a more significant factor in determining the lift reduction and altering stall behaviors. It is also found while the larger roughness advances the aerodynamic stall, the smaller roughness tends to prevent deep stall at high incident angles. PIV results also suggest that staggered distribution pattern induces higher fluctuations in the wake flow than the aligned pattern does. Results imply that distributed LE roughness with large element sizes are particularly detrimental to aerodynamic performances, while those with small element sizes could potentially serve as a passive control mechanism to alleviate deep stall conditions at high incident angles. Keywords: Distributed roughness, Surface pressure, Particle Image Velocimetry, Aerodynamic stall, Flow separationhttp://www.sciencedirect.com/science/article/pii/S2095034918301107 |
| spellingShingle | Yan Zhang Effects of distributed leading-edge roughness on aerodynamic performance of a low-Reynolds-number airfoil: an experimental study Theoretical and Applied Mechanics Letters |
| title | Effects of distributed leading-edge roughness on aerodynamic performance of a low-Reynolds-number airfoil: an experimental study |
| title_full | Effects of distributed leading-edge roughness on aerodynamic performance of a low-Reynolds-number airfoil: an experimental study |
| title_fullStr | Effects of distributed leading-edge roughness on aerodynamic performance of a low-Reynolds-number airfoil: an experimental study |
| title_full_unstemmed | Effects of distributed leading-edge roughness on aerodynamic performance of a low-Reynolds-number airfoil: an experimental study |
| title_short | Effects of distributed leading-edge roughness on aerodynamic performance of a low-Reynolds-number airfoil: an experimental study |
| title_sort | effects of distributed leading edge roughness on aerodynamic performance of a low reynolds number airfoil an experimental study |
| url | http://www.sciencedirect.com/science/article/pii/S2095034918301107 |
| work_keys_str_mv | AT yanzhang effectsofdistributedleadingedgeroughnessonaerodynamicperformanceofalowreynoldsnumberairfoilanexperimentalstudy |